+ Text Only Site + Contact STI Help Desk + Search the NTRS Database
	Back to STI home page   Following are the non-digitized 16mm films comprising the rest of the LaRC collection.   Go back to the digitized films listing. (1) The Sonic Inlet (2) Aerodynamic Noise Test With and Without Engines Running on Landing 16mm, Silent, Color (No. 1) The Sonic Inlet (No.2) Aerodynamic Noise Test with and Without Engines Running on Landing 0.02-Scale X-15 Force Tests; 0.012-Scale X-15 High Angle-of-Attack Force Tests--11 Inch Hypersonic Tunnel 1958 16mm, Silent, Color, 120ft., 3.5min 0.17 Scale Model of Navy Integrated Flight Capsule 1961 16mm, Silent, Color, 225ft., 6.5min. 0.17-Scale Model of Navy Integrated Flight Capsule 1960 16mm, Silent, Black & White, 125ft., 3.5min 0.17-Scale Model of Navy Integrated Flight Capsule 1961 16mm, Silent, Color, 107ft., 3min. 0.17-Scale Model of Navy Integrated Flight Capsule 1961 16mm, Silent, Black & White, 118ft., 3.5min. 0.17-Scale Model of Navy Integrated Flight Capsule, Test No. 2 Wallops Island, VA 1961 16mm, Silent, Color, 90ft., 2.5min. 1/10-Size Model F-86 with Twin Hydro-Skis. Gross Weight, 20,000 Pounds. 16mm, Silent, Color, 60ft., 2.5min. 1/13.33 Scale Model of Preliminary Design Martin XP6M-1 Flying Boat 16mm, Silent, Black & White 1/9-Scale A3J-1 Radio-Controlled Model Spin and Recovery Tests 1960 16mm, Silent, Color, 1475ft., 40min. 1/9-Scale Radio-Controlled A3J-1 Model Parachute Tests 1959 16mm, Silent, Black & White, 100ft., 3min. 1/9-Scale Saturn Model 1960 Originally recorded in 16mm, Silent, Color, 140ft., 5min. 10' P.T. XA-26 Sweep and Dihedral Tests 1943 16mm Sweep and dihedral tests and stall studies of a simplified wing-fuselage combination of a 0.2375 scale model of the Douglas A026 airplane were made in the 19 ft. pressure tunnel. The wing characteristics were; aspect ration 9.08 taper ratio 2.21; root section NACA 652-215 (a=0.8); tip section NACA 652-215 span flap deflected 0-degrees and 55-degrees; aileron drooped 0-degrees and 25-degrees; dynamic pressures 50, 35, and 30lb/aq.ft.; RN's 3.6, 3.1, and 2.8x10 [6th power]; Mach nos. 0.12, 0.10, and 0.09; angles of attack from -4.6-degrees to 15.4-degrees; and lift coefficients from 0.79 to 2.78. Sweep configurations were: normal sweep, 20% chord line straight; sweep forward, -10% chord line straight; and sweep back, 110% chord line straight. 10,000 KVA Heating Facility 1958 16mm, Silent, Color, 585ft., 16min. 116-E Tank 16mm, Silent, Black & White 11-Inch Ceramic Heated Tunnel 16mm, Silent, Black & White, 1400ft., 39min. 131-X with Hydrofoil PB2Y-3 1943 16mm Tank tests of a 1/8 scale dynamic model of PB2Y-3 with a hydrofoil to relieve bow spray by unloading the hull. The span of the hydrofoil is 15.9 in. and the chord is 4.2 in. The full-size conditions are 76,000# gross load, center of gravity of 28% MAC, 1200 BHP/engine, 40-degrees flap deflection, neutral elevators, and acceleration of 1ft/sec./sec. The model was tested without hydrofoil from 0 to 16 fps; with hydrofoil 5.3in. forward of C.G. and 8.2in. forward of C.G.; incidence of 7-degrees and 9-degrees to baseline; gap, hydrofoil to keel, 2/3 and 1 1/4 chords from 0 to 14 and 0 to 16 fps. 133 Tank 16mm 143 E-XP441 16mm, Silent, Black & White 1520 Javelin Payload-Antenna Erection Tests in the Langley 41-Foot Vacuum Sphere-Requested by Goddard Research Center 1961 16mm, Silent, Black & White, 1450ft. 16 Foot Transonic Tunnel Fire (about 1952) 16mm, Silent, Black & White 16-Foot HST Parachute- Schuller; Failure Tests of Parachutes 16mm Strength, failure, and stability tests made in 16ft. high-speed tunnel of 10 parachutes to determine airspeed at which failure occurs. Two different sizes were tested; 7 having a maximum diameter of 38in. and a mouth diameter of 34in., the only difference being in a shroud-line-canopy attachment; and 3 having a mouth diameter of 54in. and identical to each other. 19' Lockheed Wing No. 2 Tufts 1930 16mm Depicts tuft studies made on the Lockheed Wing #2 in the 19-foot pressure tunnel. The tests were made at a density of approximately 70 pounds per square foot; flap deflections of 0%, 25%, 50%, 80%, and 100%, and an angle of attack range from 6-degrees to 20-degrees. 19' P. T. Lockheed Wing No. 1 Tufts 1939 16mm Depicts tuft studies made on the Lockheed Wing # 1 in the 19-foot pressure tunnel. The tests were made at a density of approximately 70 lb. per sq. ft.; flap deflections of 0%, 25%, 50% and 100%; and an angle of attack range from -5-degrees to 20-degrees. 19' P. T. Test 72 1943 Stall studies were made of a semi-span model of the XB-36 airplane in the 19-foot pressure tunnel. The model wing used full span flaps, the in board sections, separated by the nacelles, being the slotted type and the outboard section being of the balanced split type. The tests were run at a Reynolds number of 8,900,00 and a Mach number of 0.17. Tests were run at angles of attack from 12-degrees to 18.6-degree with the flaps not deflected; tests were run at angles of attack from -3.8-dggrees to 18.8 degrees with the inboard flaps deflected 40-degree and the outboard flaps not deflected; tests were run at angles of attack from -3.7degrees to 16.9-degrees with the inboard flaps deflected 40-degrees and the outboard flaps deflected 50-degrees. 19' P.T a-26 Tufts 1943 16mm Stall studies were made, by means of tufts, over the 0.2375-scale model of the Douglas A-26 airplane in the 19ft. pressure tunnel. At flap deflections of 0-degrees, tests were made over a range of angles of attack from 0-degrees to 17-degrees, with the oil cooler duct exits closed then fully opened. At a flap deflection of 55-degrees with oil cooler duct exits closed the angel of attack range was from -7-degrees to 13-degrees. With flaps deflected at 55-degrees and aileron deflected 25-degrees and oil cooler duct exits closed and fully opened, the angle of attack range was from -4-degrees to 8-degrees. Low-drag duct entrance was installed in right wing with exit full open and airplane duct entrance installed in left wing with exit closed and tested over an angle of attack range from 2-degrees to 6-degrees. Oil cooler duct entrances were removed and replaced by filler blocks and tests were made over a range of angles of attack from 4-degrees to 13-degrees. 19' P.T. Pt. III B-32 Testing 16mm Stall tests were made, by means of tufts, were made in the 19 ft. pressure tunnel on a 1/8 scale model of the B-32 equipped with propellers operating at 40% normal rated power for RN approximately 2.6x10 [6th power]. Stall progression is presented for the model, with #4 and #5 nacelle afterbodies tested for various configurations with leading edge gloves and trailing edge extensions, and for double slotted inboard flaps, deflected 40-degrees. Transition was fixed at 10% of the original wing chord. The trailing edge extensions cover 0.6 span. The angles of attack range from 0.1-degree to 15.7-degrees and the lift coefficients range from 0.5 to 2.62. 19' P.T. Tests 112- Part II 16mm Stall studies were made, by means of tufts, in the 19-foot pressure tunnel on a 1/14-scale model of the consolidated B-36 airplane. The model was equipped with midchord slots on the outer wing panels ahead of the ailerons; partial span, single-slotted flaps; and no propeller. RN was approximately 4.5x10 [6th power]; flap deflections were 20-degrees, for the take off, and 40-degrees, for landing; angles of attack range from 0.4-degrees to 19.4-degrees; and lift coefficients ranged from 0.40 to 1.96. 19' P.T. B-32 Testing 16mm, Silent, Black & White Stall tests were made, by means of tufts, in 19 ft. pressure tunnel on 1/8 scale model of the B-32 with propellers operating at 40% normal rated power and RN approximately 2.6x10 [6th power]. Stall progressions are presented for the model, with flaps neutral, testing individually trailing edge extensions, leading edge gloves, and nacelle afterbodies #2 and #3. Combination of the #3 afterbody with trailing edge extensions, cowl flaps at 10-degrees and closed and intercooler flaps closed and open are included. Trailing edge extensions are 1.5 in. wide and cover 30% span. The angles of attack range from 0-degrees to 12.8-degrees and lift coefficients range from 0.08 to 1.16. 19' P.T. B-33 Shield (43"" H/S Test) 19' P.T. B-33 Tufts 16mm Stall studies were made by means of tufts on a 12% model of the B-33 airplane in the 19-foot Pressure tunnel. Tests were run on the normal wing and on the wing with a semi-circular spoiler between the inboard nacelle and fuselage; with rated power, 25% rated power, and with propellers windmilling; with flap deflections of 0-degrees and 40-degrees; with the control surfaces neutral; with R.N.'s of 4.72, 1.68, 3.17, 3.92, 3.84, 1.57, 2.15, 1.91, and 4.64x10 [6th power]; and with angles of attack ranging from 0-degrees to 20-degrees. 19' P.T. B-33 Tufts, Revised 16mm Presents stall studies on the wings of the Martin B-33 by means of tufts in the 19-foot pressure tunnel. The original wing was revised by building in more geometric washout from the outboard nacelle to the tip, thus giving the wing a total geometric washout of 5-degrees. The tests were run on the revised wing with propellers windmilling and with rated power; control surfaces neutral; flap deflection of 0-degree and 40-degrees; R.N.'s of 4.7, 4.01, 1.98, and 1.67x 10 [6th power]; and angles of attack ranging from 0-degrees to 20-degrees 19' P.T. F6F Tufts 16mm Stall studies were made, by means of tufts on a 1/3 simplified scale model of the Grumman F6F airplane with a low-drag wing; modified slotted flaps and dive brakes at the flap deflections 50-degrees and 4-degrees, lip angles 0-degrees and 60-degrees up, RN 5.6x10 [6th power] angles of attack from -4.9-degrees to 16-degrees and lift coefficients from 0.02-1.85. 19' P.T. Test 110-Part II 16mm Stall tuft studies were made in the 19 ft. pressure tunnel on the 1/4 scale model of consolidated B-36 airplane with sharp edge spoilers located on wing leading edge extending from center nacelle to inboard nacelle and from inboard nacelle to fuselage. Tests were made at 40% and full rated power; gross weights 3400,000 lbs. and 265,000 lbs at sea level; RN's 2.45, 2.46, and 2.48x10 [6th power]; inboard flaps deflected 0-degrees, 20-degrees, and 40-degrees, outboard flaps deflected 0-degrees and 50-degrees; angles of attack ranging from -1.6-degrees to 21.7-degrees; and lift coefficients ranging from -0.02 to 2.31. 19' P.T. Test 112- Part 1 1944 16mm Stall studies, by means of tufts, were made in the 19 ft. pressure tunnel on a 1/14 scale model of the consolidated B-36 airplane to determine an acceptable wing configuration. For the tests the propellers were removed and the R.N. was approximately 4.5x10 [6th power]. Tests were made using NACA modified wing outer panel with flaps retracted; double-slotted, partial-span flaps deflected 20-degrees and 50-degrees; from 0.1-degrees to 21.1-degrees; and lift coefficients ranging from .01 to 2.03. Tests were made using CVAC wing outer panel with mid-wing slots; with flaps retracted; single slotted, full-span flaps deflected for take-off (inboard flaps 20-degrees, outboard flaps 50-degrees), landing (inboard flaps 40-degrees, outboard flaps 50-degrees), and 50-degrees; at angles of attack ranging from 0.1-degrees to 21.1; and lift coefficients ranging from .06 to 2.19. 19' P.T. Test No. 110-Part 1 Depicts stall studies of the wing of the Consolidate-Vultee XB-36 airplane in the 19-Foot pressure tunnel. The tests were run with inboard flaps deflected 0-degree and 40-degree; outboard flaps deflected 0-degree and 50-degree; with rated power, 40-percent rated power propellers windmilling, propellers removed; with gross weights at sea level of 265,000 and 340,000 lbs.; with RN's of 2.53, 2.56, 2.6, 5.5, 5.1, and 5.4x10 [6th power] with angle of attach range from -1.5-degree to 21.6-degree; and with lift coefficients ranging from -0.023 to 2.111. 19' P.T. TEST P-36A Tufts 16mm 19' P.T. Tuft Test No. 11 16mm Tuft studies on wings were made in the 19ft. pressure tunnel. 19' P.T. XF14C Tufts 16mm Stall studies of the 0.32 scale model Curtiss F14C-2 airplane were made by means of tufts in the 19 ft. pressure tunnel. Tests were run with propeller off, windmilling, or with a thrust coefficient of 0.06; flaps neutral or down 50-degrees; controls neutral or ailerons drooped 15-degrees; slats open or closed; cowl flap at 0-degrees or 50-degrees; belly flap at 0-degrees or 22-degrees; RN's of 5.7, 5.5, or 5.8x10 [6th power]; and angle of attack range from 0-degrees to 19-degrees. 19' P.T. XF6F Tufts 16mm Stall Studies, by means of tufts, were made of a 1/3 scale simplified model of the Grumman F6F airplane, with a low drag wing, in the 19-ft. pressure tunnel. Tests were made with a short unfaired cannon, long cannon with rounded fairings, 6 gun ports, 6 gun ports and radar fairing with no fillet, and 6 gun ports and radar fairing with small fillet; extensible slotted flaps at 35-degrees. Tests were run at R.N. of 6.15x10 [6th power] and at angles of attack ranging from 8.3degrees to 17-degrees. 19' P.T. XP-67 16mm Tuft studies were made of the McDonnell P-67 full-scale nacelle without power in the 16 ft. high-speed tunnel. General views presented of inboard and outboard duct inlets. Tests made on inboard duct inlet with cooling flap positions fully closed, high speed and fully open at angles of attack 0-degrees, 5-degrees, and 9.5-degrees and indicated airspeeds of 150 and 200 MPH. 19' P.T. XTB2D-1 1944 16mm Stall studies were made in the 19 ft., pressure tunnel on a 0.30 scale semispan model of the Douglas TB2D-1 airplane with endplate seal and fillet and with deflections 30-degrees and 0-degrees; RN's 5.07, 5.06, and 5.32x10 [6th power]; Mach no. 0.12; angle of attack range from -7.9-degrees to 17.3-degrees; and lift coefficient range from-.185 to 2.715. Pull ups are presented on inboard panel from angle of attack 8.1-degrees to 19.3-degrees and on outboard panel from 9.2-degrees to 17.3-degrees. 19' P.T. XTB2D-1 1943 16mm Stall studies were made in the 19-foot pressure tunnel on a model of the Douglas TB2D-1 airplane with endplate seal; fillet off; spoiler on; radar off and on racks off and on; large vane; 2 torpedoes off and on; 4000 lb. bomb off and on; flap deflections 0-degrees and 55-degrees; roll flap deflection 0-degrees to 30-degrees; unmodified 16in. and modified 17 in. oil cooler with maximum and minimum flow; at Mach no. 0.12; RN's of 5.22, 5.27, 5.3, 5.38, and 5.14x10 [6th power]; angles of attack from -5.9 to 16.30-degrees and lift coefficients from -0.188 to -2.615. Pull-ups on inboard panel shown for angles of attack from 9.2-degrees to 14.2-degrees. 19' P.T.Martin Design 195 Tufts 16mm Stall studies, by means of tufts, were made in the 19-ft. pressure tunnel of the 1/6 scale model of the proposed low-drag wing for the Martin design #195 airplane. For all tests, the propellers were windmilling. Tests were made with flaps neutral; NACA slotted flaps deflected 25-degrees and 35-degrees; split flaps deflected 30-degrees and 60-degrees; RN's 4.78, 4.75, 4.85, and 4.87x10[6th power]; Mach nos. 0.18 and 0.17; angles of attack ranging from 2.4-degrees to 21.3-degrees; and lift coefficients ranging from .28 to 2.22. 19' Pressure P. T. P-51 1943 16mm Depicts stall studies made by means of tufts on the North America XP-51 airplane with low drag wing. Tests were made on the wing alone, on the wing and fuselage, and on the wing, fuselage, and fillet. The flap deflection angeles were 0-degrees and 50-degrees; the RN was 5.13x10 [6th power] the angle of attack range was 2.4-degrees to 22.4-degrees; and the lift coefficient range was from 0.27 to 2.06. 19' PT Calibration Tests 16mm, Silent, Black & White 1948 Spin Test 16mm, Silent, Black & White 1956-76 Full Scale Tunnel Free Flight Model (NASA Model) with Leading Edge Devices 16mm, Silent, Black & White 19-Foot Stall Studies of a Simplified F6F With Conv Wing 16mm 24-Inch HST Bomb Fuse AN-M-100 1942 16mm Arming time and functioning tests were made in 24 high-speed tunnel on the Army-Navy M-100 bomb fuse at velocities ranging from 363 to 412 MPH. 24-Inch HST Bomb Fuse M-110 16mm Supplementary arming time and functioning tests were made on bomb fuses WXS-7, 8, 9, 10, 12, 13; WX-20 and 32; 1-M101 and 2-M101 in the 24-inch high-speed tunnel at velocities of 199, 200, 201, 397, 399, and 500 MPH. 24-Inch HST Bomb Fuse M-110, Peco West 16mm Arming time and functioning tests were made in the 24-inch high-speed tunnel on M-110 bomb fuses of the Peco, Westinghouse, and Richard-Westinghouse types at velocities covering a range from 199 through 515 M.P.H. 24-Inch HST Bomb Fuse M-110, Phase 1 16mm Arming time and functioning tests were made of Army M-100, 103, and 110 bomb fuses in the 24-inch high-speed tunnel. Various velocities used covered a range from 103 through 404 M.P.H. 24-Inch HST Bomb Fuse M-110, Phase 2 Arming time and functioning tests were made on the Army M-110 bomb fuse in the 24 High-speed tunnel at velocities of 248, 555, 574, and 573 MPH. 24-Inch HST M-110 Bomb Fuse 1942 16mm Arming time and functioning tests were made in the 24-inch High-speed tunnel on the Army M-100 bomb fuse at velocities ranging from 101-370 M.P.H. 24-Inch HST Radio Masts 16mm Tip deflections of a Naval aircraft radio antenna were measured in the 24' high-speed tunnel at 0-degrees and airspeeds from 100 to 600 MPH. 4-Foot SSPT Schileren 1949 Conference 16mm, 290ft., 16min. 8' HST P-47 Flutter 1942 16mm Flutter tests on P-47 fin-rudder unit were made in the 8-foot high-speed tunnel over an approximately true tunnel speed range from 200 to 460 M.P.H. Failure occurred at approximately 468 M.P.H. (410 M.P.H. indicated). 8' HST P-47 Flutter-Second Test 16mm Flutter tests of the Republic P-47 fin-rudder unit wee made in the 8-foot high-speed tunnel. 8' HST P-47 Metal Rudder Flutter 16mm Flutter tests of the Republic P-47 rudder were made in the 8-foot high-speed tunnel. 9x6 Panel Flutter Tests 1959 16mm, Silent, Black & White, 180ft., 5min. 9x6-Foot Thermal Structures Tunnel 1958 16mm, Silent, Color, 385ft., 11min. A Demonstration of Computer-Aided Structural Design 1968 16mm, Sound, Color, 221ft., 6.6min. A Group of High Speed Configuration Take-Offs and Landings 16mm, Silent, Color, 400ft., 16min. A Study of Ditching 16mm, Silent, Black & White The Army and Navy requested the NACA to investigate the behavior of military air planes while ditching in order to obtain information that would help reduce the loss of personnel in that operation. The only feasible method appeared to be the ditching of dynamically similar scale models of the airplanes. Although their was uncertainty as to exactly how accurately the behaviors of the models reproduced those of the full-size airplane, the comparative results gave useful information. Failure of a part of the full-size airplane is simulated by removing the corresponding part of the model before ditching. The models tested were the SB2C-1, B-17, B-32, B-24, B-25, and B-29. Tests were made in Tank # 2 and using the seaway catapult. Most of the models dived when ditched, but than can be prevented by the use of a hydroflap, hydrofoil, or hydrospoiler under the nose or by reinforcement of the bomb-bay doors to prevent their failure when ditching. Through the cooperation of the Army Air Forces, it was possible to ditch and Actual B-24 under controlled conditions. The airplane was ditched in the James River. Despite extensive reinforcement the airplane was damaged severely. From the comparison of the ditching of the full-size B-24 with the tests of models it was concluded that tests of model give very good approximations of the behavior of the full-size airplanes. A Study of Low-Speed Flight Characteristics of Powered Lift Jet Transports 1965 16mm, Sound, Color, 670ft.,19min. A Study of the Flow Over Several Thick Symmetrical Airfoils. 16mm, Silent, Black & White, 690ft., 28min. A Study of the Use of Canard Surfaces as an Aid in Recovering from Spins and Preventing Directional Divergence Near the Stall Film 1955 16mm, Silent, Black & White A Technique for Determining Wake Location from a Helicopter in Flight 1961 Originally recorded in 16mm, Silent, Color, 660ft., 15min. A Visual Aid for Determing the Characteristics of Gases Vented Into a Supersonic Stream 1961 16mm, Silent, Black & White, 285ft., 7min. A Water Immersion Technique for Zero Gravity Simulation of Astronaut Ingress-Egress Maneuvers 1965 16mm, Silent, Black & White, 290ft., 8min. A Wind Tunnel Guest Response Technique 1965 16mm, Sound, Color, 170ft., 4.5min A-26 16mm, Silent, Black & White, 253ft. A-57 H/S Ejection Test and OFO/RMS Payload: Part II- A-47 H/S 16mm, Silent, Black & White Abalation Tests in 700-kw Arc Jet. 1961 16mm, Silent, Black & White, 120ft., 3min. ABMA 20 MC Antenna Release Tests in 41-Foot Sphere 1959 16mm, Silent, Black and White, 6000ft., 2hr. 49min. ABMA Jupiter Nose Cone Advanced Materials Evaluation Program 1960 16mm., Silent, Black & White, 300ft., 9min. ABMA Payload 16 Antenna Release Test 1959 16mm, Silent, Black & White, 3160ft., 88min. A-Bomb (Print) 16mm, Silent, Black & White News of the day presents Atom Bomb Blast No.5. World's most astounding man-made phenomenon filmed by cameramen of U.S. Navy, Coast Guard, Army Air Forces and American newsreels of underwater explosion of the atomic bomb during Operations Crossroads in the Bikini Lagoon. Access 16mm, Silent, Color Aces, Washington Show 1964 165mm, Sound, Color Acoustic Exposure Tests for Squirrel Monkeys 16mm, Silent, Color, 420ft., 11.6min. Advanced Composite Aileron 1968 16mm, Sound, Color 13min. Advanced Composite Elevator for the Boeing 727 Aircraft 1981 16mm, Sound, Color, 14min. Advanced Composite Vertical Fin Component for L-1011 Aircraft 1984 16mm, Sound, Color 11min. Advanced Composite Vertical Fin-Manufacturing 1982 16mm, Sound, Color, 600ft. Advanced Composite Vertical Fin-Quality Assurance 1982 16mm, Sound, Color, 400ft. Aerodynamic and Deployment Characteristics of Multistage Canopy and Suspension Line Reefing System for a Twin Keel All Flexible Parawing. 1970 16mm, Silent, Color, 120ft., 3.5min. Aerodynamic and Flow Visualization Studies of Two Delta Wing Entry Vehicles at a Mach Number of 20.3 1973 16mm, Silent, Color, 5min. Aerodynamic and Hydrodynamic Characteristics of Models of Some Aircraft-Towed Mine Sweeping Devices 16mm, Silent, Black & White, 465ft, 13min Aerodynamic Characteristics of Parachutes at Mach Numbers from 1.6 to 3 1961 Originally recorded in16mm, Silent, Black & White, 1000ft., 28min. Aerodynamic Characteristics of the X-15/b-52 Combination 16mm, Silent, Black & White, 641ft., 18min. Carry loads, aerodynamic interference effects and drop characteristics of x-15 through b-52 flow field Aerodynamic Drag and Stability Characteristics Towed Inflatable Decelerators at Supersonic Speeds 1962 16mm, Silent, Black & White, 90ft., 2.5min. Aerodynamic Heating and Deceleration During Entry Into Planetary Atmospheres 1962 Originally recorded in 16mm, Silent, Black & White, 1100ft., 29min. Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers up to 14 1958 Originally recorded in 16mm, Silent, Black & White 330ft., 9min. Aerodynamic Research Relative to Variable Sweep Aircraft 1961 16mm, Silent, Color, 275ft., 7.5min. Aeroelastic Phenomena and Research Techniques 1972 16mm, Silent, Color, 11min. Aeroelastic Tests of an Eight Percent Scale Saturn C-1 Block II 1963 16mm, Sound, Color, 188ft., 5.25min. Aeroplastic Phenomena and Related Research 1973 16mm, Sound, color, 482ft., 13.5min. AIR AND SPACE (For Paris Air Show) 1977 16mm, Silent, Color Air Cushion Landing Gear 1966 16mm, Silent, Color Air Cushion Landing Gear 1966 Air Force Day Film--194819' P. T. P-51, 194019' Rough Water Landings of a 1/8-Scale Model of a Grumman JRF-5 with and without Hydro-Skis (Model Film Data, Dec. 1948) 1948 16mm, Silent, Black & White, 90ft, 4min Air Force Movie--Goose with Skis 16mm Air to Air Tracking Using an APQ-35B Radar System 16mm, Silent, Black & White/Color Aircraft Crash Tests Composite Data Film 'A' Wind 1978 16mm, Silent, Color, 788ft., 22min. Aircraft Structural Testing in True Temperature Supersonic Jets 1956 16mm, Silent, Color, 120ft., 3min. Aircraft Trailing Vortices 1970 16mm, Silent, Color, 430ft., 12min. Aircrafts 16mm, Silent, Color Air-Flow Characteristics on a 40-Degree Sweptback Wing as Indicated by Surface Tufts. 1957 16mm, Silent, Black & White, 100ft., 3min. Air-Flow Visualization for Several Rotor Configuration Models Operating in the Static Thrust Condition 16mm, Silent, Black and White, 210ft., 9min. Airline Pilot Visual Scanning Studies Conducted Jointly by NASA LRC/AMES at Piedmont Airline Training Facility 1977 16mm, Sound, Black & White, 270ft., 7.5min Ames Laboratory 6'x6' Wind Tunnel 16mm, Color, 376ft. Construction and operation of the 6-foot by 6-foot supersonic tunnel at Ames Aeronautical Laboratory are presented. Several views of the power plant which furnishes power for the operation of this tunnel are also shown. Ames Laboratory in Action 16mm This is a publicity film showing aerial views of Langley, Aeronautical Laboratory, Lewis flight Propulsion Laboratory, and Ames Aeronautical Laboratory. Since the film was made by and for AAL, views of AAL laboratory and its activities are presented, including views of AAL Sheet Metal Shop, views of various wind tunnels and tests carried on in them. Actual views, schematic diagrams, and tests are shown in the 40x80-foot, the two 7x10-foot, the 16-foot high-speed, the 12-foot pressure tow-turbulence, and the 1x3-foot tunnels. An ice prevention test on and airfoil was made by mounting an airfoil on top of a C-47 in flight, and the wing flow test was made on a model mounted on the wing of a P-51 in flight. Full-scale airplanes are P-512, P-39, C-47, P-80, and F4F. Instruments, designed and assembled by personnel at AAL, are also presented. An Advanced Composite Stabilizer for the Boeing-737 1982 16mm, Sound, Color, 6min. An Energy Absorption Process Employing Frangible Metal Tubing 1964 16mm, Sound, Color, 290ft., 8min. An Evaluation of Linearized Vortex Theory as Applied to Single and Multiple Rotors Hovering In and Out of Ground Effect 1959 16mm, Silent, Black & White, 190ft., 5min. An Experimental Study of the Effect of Downwash from a Twin Propeller VTOL Aircraft on Several Types of Ground Surfaces 1962 16mm, Silent, Color, 670ft., 18.5min. An Exploratory Investigation of Jet Blast Effects on a Dust Covered Surface at Low Ambient Pressure 1961 Originally recorded in16mm, Silent, Black & White, 702ft., 19.5min. An Investigation of Resonant, Nonplanar Free-Surface Oscillations of a Fluid 1962 16mm, Sound, Color, 275ft., 7.5min. An Investigation to Determine the Effect of Lithium Hydride as an Internal Coolant in Stainless Steel and Molybdenum Models 1961 16mm, Silent, Color, 965ft., 27min. Animation and 30 Cell Manometer Records for Ames Conference. 1950 1950 16mm Apollo 13 Review Board Test Support Operations 16mm, Silent, Color, 8min. Apollo-Lunar Orbital Rendezvous Technique Originally recorded in 16mm, Sound, Color, 219ft., 5min. Apollo-Soyuz 1975 Apparatus for Study of Electomagnetic Wake Propagation Through an Ionized Gas 1958 16mm, Silent, Color, 140ft., 4min. Arial of Scout 16mm, Silent, Black & White Assembling and Testing of the Parachute Recovery System for the Temco Corvus Missile at Wallops Island, VA 16mm, Silent, Color, 15.5min. Assembling and Testing of the Parachute Recovery System for the Temco Corvus Missile at Wallops Island, Va. 1958 16mm, Silent, Color, 560ft., 15.5min. AST Structural Panel Program Weldbrazed Panels 8-5-74 1974 16mm, Sound, Color, 400ft., 10min. Astronaut Personality Clips (John Young STS-1 Pilot) 16mm, Silent, Color Astronaut Shepard Reports on Space 1962 16mm, Sound, Color, 720ft., 20min. Atlas Missile Test Project 16mm, Silent, Color Automobile Dual Braking 1967 16mm, Sound, Color, 432ft., 12min. AWT XPB2M-1 Flutter 16mm B-17 Training Film Catapult 16mm Catapult tests were made, using the seaway catapult at Langley Field, VA., to determine the ditching performance of the Army B-17F airplane. For the tests a 1/16 scale dynamic wooden model was used. The flaps were semi-fixed in the down position. Representative power-off landings were made from high, medium, and low altitudes, at angles of attack of 3 1/2-degrees, 7-degrees, and 10-degrees and airspeeds of 98, 110, and 122 MPH, in smooth water, across the waves and along the waves for the complete model and for the model in a damaged condition in which failure of the nose window, bomb-bay doors, camera hatch, lower turret, rear entrance door, tail wheel well, and rear gunner's entrance door simulate. Two three-wheel landings at angle of attack of 0-degrees and 135 MPH airspeed are also shown. Smooth water tests were made with the bomb-bay doors and gun turret in position and hydroflap installed to increase the landing run and to keep the nose clear. B-19 1/20 Model Ditching Tests (Part II Rough) 16mm, Silent, Black & White Ditching tests were made by using the seaway catapult at Langley Field, VA., on a 1/20-scale model of the Army B-29 airplane in rough water. Scale strength flaps were used and all values; weight of 105,000 lbs., C.G. at 25% MAC and 32 in. above the fuselage center line; attitude angles of 1-degree and 9-degree, flap deflections of 45-degree and airspeeds of 104 and 128 MPH; refer to the full-scale airplane. Rough water tests were made with nose window, nose wheel door, main wheel doors, bomb-bay doors, section of fuselage between the bomb-bay doors, camera hatch, main entrance door, and tail skid door removed to simulate their failure. Runs were made with wave crests parallel and perpendicular to flight path in waves from 5-12 feet high. Landings were made with one wing low and initial contract on crest and on windward side of wave. B-24 Army Training Film Catapult 16mm, Silent, Black & White Catapult tests were made, using the seaway catapult at Langley Field, VA., to determine the ditching performance of the army B-24 airplane. A 1/16-scale dynamic wooden model was used with various structural parts, as the bomb-bay doors, nose-wheel doors, and entrance hatches removed to simulate a damaged condition, and C.G. at 28.5% MAC. Representative power off landings were made with the flaps down in smooth water, across waves, and along waves, for light and heavy weight conditions, in tail down, 2-wheel and 3-wheel landing attitudes. The first series of runs were made with the bomb-bays removed and complete bulkhead behind the bomb-bay. The last series were made with bomb-bay doors partially retracted so that only the flat portion of the fuselage was open. B-24 Ditching Instrumentation 16mm B-24 Ditching with Hydro-Scoop 16mm, Silent, Black & White A method considered for improving the water performance of land planes during ditching requires a hydro-scoop to be installed on the rear part of the fuselage. To determine the full-scale hydrodynamic characteristics of a hydro-scoop, one was installed on a B-24 airplane which was ditched at the AAF Proving Ground Command at Eglin Field, Florida. The experiment was made cooperatively by the NACA; which developed, designed, and built the instrument; and the AAF. A NACA photo-observer incorporating instruments to record airspeed, attitude and longitudinal deceleration was a part of the instrumentation. Eight gun-sight cameras were equipped with special wide -angle lenses and installed in waterproof housings. The B-24 was flown to the ditching site by radio control from the C-45 mother plane. It had been planned to land the airplane on the water at a high (near stall) attitude with a low forward speed. However, due to the pilot's inability to judge the airplane's altitude, it contacted the water at a 1-degree nose-down attitude, with a speed of 107 MPH, and a rate of descent of 9 fps. Because of the temporary failure of the instrument radio switch, the photo-observer and damage cameras did not start recording until 1 second after impact, at which time the damage cameras were submerged, and the record of the damage occurring during ditching had to be obtained from observation by divers. The airplane was severely damaged, leaving a stream of debris in its wake, and sank within 6 minutes. Since the hydro-scoop was designed to be effective in a high-attitude landing, the experiment did not give and evaluation of the effectiveness of the hydro-scoop as a ditching aid. Graphs of attitude and deceleration showing the time-history of the airplane during the ditching run are presented. The airplane ran only 3 lengths after contacting the water, and had a maximum deceleration of 4 G, which occurred immediately after contact. B-24 Tufts 19' P.T. 16mm, Silent, Black & White B-24 Wheel Pictures 16mm Presents a flight investigation of the effects of landing impact on horizontal tail loads. Landings were made with the main wheels in one of 3 positions; (1) initially stationary but free to rotate, (2) prerotated, (3) locked with brakes. Landings were made at ground speeds of 96, 101, 103, 107, 114, and 122 MPH; at vertical velocities of 2.1, 2.2, 4.0, 4.2, 6.7, and 6.9 FPS; at attitude angles of -0.0, 3.2, 2.9, and 4.8-degrees; normal accelerations 0.6g, 0.8g, 1.05g, 1.12, and 1.55g. The landing gear frequency and frequency of the horizontal tail in symmetrical bendings are substantially the same about 7 cycles/sec. Occasionally both main wheels touch at these same time and the fore-and-aft oscillations are in phase. When this happens the tail approaches resonance with the landing gear, and tail vibrations of increasing amplitude occur, although the amplitudes of the landing gear oscillations are decreasing. Tail loads are greatly reduced when the wheel oscillations are eliminated by pre-rotation or braking. B-32 Airplane 19 Foot Pressure Tunnel Test 109 16mm, Silent, Black & White B-32 Part 4-- Tufts 19' P.T. 16mm, Silent, Black & White B-32 Part IV Tufts 19' P.T. 16mm Stall tests were made, by means of tufts, in the 19 ft. pressure tunnel on a 1/8 scale of the B-32 at an RN approximately 2.6x10 [6th power]. Stall progression for the model is presented with propellers operating at 40% normal rated power windmilling, and off; with various configurations - leading edge gloves and 60% span trailing edge extensions added, cowl flaps open10-degrees and closed, intercooler flaps open and closed, standard nacelles, nacelle afterbodies #3 and #4 - at flap deflections of 0-degrees and 40-degrees, angle of attack range from 0-degrees to 12.9-degrees, and lift coefficient range from 0.05 to 2.57. Transition was fixed at 10% of the original wing. B-32 Testing 16mm Stall Tests were made, by means of tufts, in the 19-foot pressure tunnel on a 1/8 scale model of the B-32 with propellers operating at 40% normal rated power; RN configuration, with transition fixed, through the range of flap deflection of 0-degrees, 10-degrees, 20-degrees, 30-degrees, and 40-degrees; and with the cowl flaps at 10-degrees or closed and intercooler laps closed and open. Natural transition in the clean condition is included for flap deflection of 0-degree, angle of attack range from 4.3 degrees to 11.8-degrees and loft coefficient range from 0.47 to 1.20. For the tests with transition fixed the angles of attack ranged from 0-degrees to 14.7-degrees and the lift coefficients ranged from 0.7 to 2.57. B-35 Test 127 16mm, Silent, Black & White Stall tests were made, by means of tufts, were made in the 19ft., pressure tunnel on a 1/8-scale model of the B-32 equipped with propellers operating at 40% normal rated power for RN approximately 2.6x10[6th power]. Stall progression is presented for the model, with 34 and 35 nacelle afterbodies tested for various configurations with leading edge gloves and trailing edge extensions, and for double slotted inboard flaps, deflected 40-degrees. Transition was fixed at 10% of the original wing chord. The trailing edge extensions cover 0.6 span. the angles of attack range from 0.1-degree to 15.7-degree and the lift coefficients range from 0.50 to 2.62. B-36 (Revised) Outboard Nacelle 16mm, Silent, Black & White Stall studies were made by means of tufts in the pressure, low-turbulence tunnel on the revised 1/4-scale model of the outboard nacelle of the B-36 airplane at RN of 1.68x10 [6th power] over a lift coefficient range from 0.49 to 0.943. Rear top view of the nacelle and three-quarter front view of the air inlets are shown. Ball Spring, Etc.--Rhode 16mm Beating the Heat 1957 16mm, Sound, Color, 650ft., 19min Bell Multi-Skin Tests in Wallops Island High Temperature Jet 16mm, Silent, Color, 380ft., 10.5min. Bell-Raytheon Structural Integrity Test of a Composite Panel Consisting of: 0.03-Inch Degassed Astrolite Sheet, 3/8-Inch-Thick Ectofoam Insulation 1/16-Inch-Thick Aluminum 1959 16mm, Silent, Black & White, 255ft., 7min. Beryllium Hemispherical Nose Models Supplied by Lockheed Aircraft Corp. for U.S. Navy Polaris Program 1958 16mm, Silent, Black & White Big Shot Viewing Test No. 6, August 24, 1961 1961 Originally recorded in 16mm, Silent, Black & White, 340ft., 9.5min. Blast Effects of Twin Variable-Cant Rocket Nozzles on Visibility During Landing on a Particle-Covered Surfaces 1964 Originally recorded in 16mm, Silent, Black and White, 1655ft., 1hr. 46min. Body Vapor Screen Tests Langley 4- by 4-foot Supersonic Pressure Tunnel. M=20 16mm, Silent, Black & White, 410ft, 17min Boeing Dyna-Soar in Unitary 1959 16mm, Silent Boeing Dyna-Soar in Unitary 16mm, Silent, Black & White Boeing Dyna-Soar In Unitary 16mm, Silent, Black & White Boeing Dyna-Soar Project. I.N. 59-187; I.N. 59-218 1959 16mm, Silent, Black & White, Boeing Dyna-Soar Tests in the Langley 11-Inch Hypersonic Tunnel 1961 16mm, Silent, Color, 140ft., 4min. Boeing Model 1 E 1957 16mm, Silent, Black & White, 225ft., 6min. Bomb Fuses 1942 A number of tests on bomb fuses were shown. 16mm Bomb Releases at Supersonic Speeds 16mm, Silent, Black & White Boron Composites in the CH 54B Helicopter 1972 16mm, Sound, Color, 500ft., 14min. Boron-Epoxy Reinforced C-130 Center Wing Box Program 1975 16mm, Sound, Color, 21min. Boy Scouts--First in Space 16mm, Sound, Color, 400ft., 11min. Buckling Strength - Curved - Combined Compression and Shear 16mm Bureau of Aero. Design #22A DR Model # 206 16mm, Silent, Black & White Landing tests and spray characteristics tests on bow, in propellers, on flaps and on tail surfaces of a 1/11-scale dynamic model of the Bureau of Aeronautics design #22ADR, class VPB airplane were made in Tank #1. For the spray characteristics tests the model was tested with gross loads of 78.1, 93.0, 107.9 and 122.7lbs.; with flaps deflected 20-degrees; stabilizers deflected -9.5-degrees to wing; C.G. at 28% MAC; and full power. As the weight of the model increased the spray remained in the propellers for increasing distances during accelerated runs. For the Landing tests the flaps were deflected 20-degrees, stabilizers deflected -9.5-degrees to wing, C.G. at 38% MAC, ? static thrust was used and the gross loads were 78.1 and 93.0lbs. The trim angles covered a range from 14.1-degrees to 4-degrees. Burning of Metal Rods in a Supersonic Jet 16mm, Silent, Color, 60ft, 2.5min Cable Splice and Spreader Arm Assembly 16mm Calm and Rough Water Ditching Investigation of a 0.043 Scale Model of a Typical Jet Transport With and Without Ditching Aids 1058 15mm, Silent, Black & White, 201ft., 5.5min. Calm and Rough Water Ditching Investigation of a 0.043 Scale Model of a Typical Jet Transport with Landing Gear Extended 1957 16mm, Silent, Black & White, 220ft., 6min. Cambridge Research Center Sounding Rocket Test at Wallops Island, Virginia 16mm, 365ft., 10min. Candidate Space Shuttle Orbiters M+20 Electron Beam Flow Studies, Long Version 1970 16mm, Silent, Color, Candidate Space Shuttle Orbiters M=20 Electron Beam Flow Studies Dec. 1969 Short Version 1969 16mm, Silent, color, 210ft., 6min. Cargo Transfer in Rough Water - Part-1 16mm, Silent, Black & White, 400ft., 16min. Carrier Landings 16mm, Silent, Black & White Catapult Ditching B-25 16mm, Silent, Black & White Ditching tests were made using the seaway catapult at Langley Field, VA., on a 1/11 scale dynamic model of the Army B-25 airplane in heavy weight condition and a no bomb-load, partial fuel-load condition; with flaps semi-fixed in the full-down position; Bombardier's window, the three-wheel doors, the entrance hatches, and the bomb-bay doors omitted. High and medium attitude landings were made in smooth water; across wind, along wave; and into wind, across waves; at airspeeds ranging from 86 to 105 MPH, weights of 22,600 and 25,800 lbs., and attitude angles ranging from 6-degrees to 13-degrees. Catapult Ditching Tests of A-26 Part 4 16mm Ditching tests were made using the seaway catapult at Langley Field, VA. on a 1/12 scale model of the Army A-26 airplane in calm and rough water. All values weight of 25, 730 lbs., C.G. at 28.4% MAC and 5.1 in. above thrust line, flaps deflected 55-degrees, attitude angle of 8-degrees, airspeed of 100 MPH; refer to the full-scale airplane. Tests were made with the nose-wheel doors, bomb-bay doors, main landing gear doors, aft end of the nacelles, and lower turret-service door removed to simulate their failure; with all-purpose nose door closed and braced open 30-degrees to the thrust in to form a hydro flap; in calm water, parallel to 2 and 3 ft. waves perpendicular to 2, 3, and 6ft. waves; at ground speeds from 68 to 122 MPH. Celestial Mechanics and the Lunar Probe 1958 16mm, Sound, Color, 327ft., 10.5min. Centrifugal Antenna Erection 1961 16mm, Silent, Black & White, 2788ft., 1hr. 22min. Ceramic Heat Exchanger 1956 16mm, Silent, Color, 280ft., 8min. Circulation in Drops 16mm, Silent, Black & White Classroom In Space-The Getaway Special 16mm, Sound, Color Cold Separation Test for the S-55B, February 1962 1962 16mm, Silent, Black & White, 910ft., 25min. Color Schlieren Motion Picture of a Cascade of 65-(4A10)06 Blade Section in Reverse in the Langley 7-Inch High Speed 1956 16mm, Silent, Color, 150ft., 4min. Combat Traction--USAF-NASA Cooperative Project 1970 16mm, Silent, Color, 320ft., 9min. Comparative Measurements of Man's Walking and in Earth and Simulated Lunar Gravity 1966 16mm, Silent, Color, 70ft., 2min. Comparison and Evaluation of Several Chemicals as Agents for Rocket-Vehicle Production of Smoke Trails for Wind-Shear Measurements. 1964 16mm, Silent, Color, 790ft., 22min. Comparison Film Skate 7 With and Without Skies 16mm Comparison Of Wind Tunnel And Flight Vortex Systems 20 Degrees Angle Of Attack 16mm, 5.53min Completely Flexible Wings With Variable Geometry 1967 16mm, Silent, Color, 130ft., 3.5min. Compressibility 16mm, Silent, Black & White Computer Simulation of Disk Galaxies 1969 16mm, Silent, Black & White, 205ft., 5.6min. Computer Simulation of Disk Galaxies 16mm, Silent, Black & White Computer Simulation of Disk Galaxies 16mm, Silent, Black & White Computer Simulation of Disk Galaxies 16mm, Silent, Black & White Computer Simulation of Spiral Galaxies 16mm, Silent, Black & White Computer Simulation of Spiral Galaxies 16mm, Silent, Black & White Computerized Circuit Analysis With Visual Input/Output 16mm, Silent, Color Computers in Aerospace Research 1964 16mm, Sound, Color, 875ft., 24min. Conference at LAL- Univ. Professors 1948 16mm, Silent Pictures were made at the University Conference on Aerodynamics of professors who came to LAL from all over the U.S. to be brought up to date on all phases of aerodynamics. Pictures were made in the 7 by 10-foot tunnel building and on the lawn of the recreation building in the West Area Consolidated--Vultee XP-92 Nose Capsule Release, Report No. 25 Consolidated--Vultee XP-92 Report No. 50 Construction of Wooden Propellers 16mm The entire process through which sitka spruce passes to become a 45ft. wind tunnel propeller is depicted. The NACA, through refusal of propeller manufacturers to make these propellers, was forced to set up a shop and train model makers to do the job. Shows special tools developed by NACA to be used on the propellers in various phases of the construction process. Control Missile John Hopkins 16mm, Silent, Black & White At the request of the Bureau of Ordnance, Navy Department, roll stabilization tests of the Johns Hopkins CTV control missile were conducted in the high speed 7' x 10' tunnel in order to obtain information concerning the roll stabilization systems employed. Motion picture records were taken during the tests at the same time the missile and aileron motions were being recorded by electrical methods. Tests were made with follow up ratios of 6/1, 4/1, 2.5/1, and 1.6/1; feed back of 100% and 200%; rate gyro at 100%, 50%, and 0; at velocities from 355 to 503 MPH; and Mach nos. from 0.483 to 0.699. Controlled Tethering in Space 1965 16mm, Sound, Color, 600ft., 16.5min. Convair B58A Model in Langley 4-Foot SPT for Test No. 233 1960 16mm, Silent, Color, 85ft., 2.5min. Convection and Radiation Heating Apparatus 1952 16mm, Silent, Color Copy Scout Test Vehicle 16mm, Silent, Color Correlation of the Ditching Performances of a 1/16-Size Dynamic Model of the Army B-24 Airplane and the Full Size Airplane 1958 16mm, Silent, Black & White, 170ft., 7min. Countersunk Rivets 16mm Presents a comparison of tightness of joints constructed by the use of 3 classes of machine-countersunk rivets for aircraft. Those of class 1 have an annular gap around the rived head caused when the hole is countersunk to a depth greater than the height of the rivet head. The height of the heads of rivets in class 2 is equal to the depth of the hole, thus forming no gap and increasing the tightness of the connection. Rivets of class 3 are those whose heads protrude above the surface. These are the tightest rivets when preformed countersunk heads are used. A still tighter flush rivet can be obtained by inserting a round-head rivet from the back and forming the countersunk head by driving. For the 2 tightest rivets, the heads protrude above the skin surface after driving. The protruding portion of the heads is removed by a flush-rivet milling tool, which may be set to shave off the heads very close to the surface. Desirable aerodynamic smoothness is obtained by painting or polishing the surface. Crash Tests of Four Identical High-Wing Single-Engine Airplanes 16mm, Silent, Color, 15.5min. Crew Motion Disturbances- Simulation of Determination of Vehicle Disturbance Due to Crew Activity 1967 16mm, Silent, Color, 310ft., 8.5min. Cutting-005in. Slots for Laminar Flow Control Airfoil 1977 16mm, Silent, Color, 145ft., 4min. Data Film on the 1/25-Scale Model of the Chance-Vought XF8U-1 Airplane--Part II 1955 16mm, Silent, Black & White, 905ft, 37min Data From a Static-Thrust Investigation of a Large-Scale General Research VTOL-STOL Model in Ground Effect. 1960 16mm, Silent, Color, 315ft., 8.5min. The model was tested at two different elevations with the wing pivot at 1.008 and 2.425 propeller diameters above the ground. The slipstream of the propellers was deflected by tilting the wing and propellers, by deflections of large-chord trailing-edge flaps, and by combinations of flap deflection and wing tilt. Tests were conducted over a range of propeller disk loadings from 7.41 to 29.70 pounds per square foot. Force data for the complete model and pressure distributions for the wing and flaps behind one propeller were recorded and are presented in tabular form without analysis. DC-3Tufts in Flight Presents tuft studies over wings and ailerons of Douglas DC-3 in Flight 16mm Deck Inlet and Planning Tail Configurations 16mm, Silent, Black & White, 185ft, 7.5min Deep Sea Diving 1961 Originally recorded in 16mm, Silent, Black & White, 800ft., 22min. Delta-Wing Hydro-Ski Configuration 16mm, Silent, Black & White, 100ft., 4min. Demonstration of Fuel Sloshing in a Sphere-1st. and 2nd. Modes 1959 16mm, Silent, Color, 125ft., 3.5min. Demonstration of In-Flight Variation of Wing Sweep With a 1/10-Scale Free Flying Model of a Variable Sweep Attack Airplane 1961 16mm, Silent, Color, 93ft., 3min. Demonstration of Structural Feed-Back Instability 1959 15mm, silent, Color 70ft., 2min. Deployment and Performance Characteristics of 5-Foot Diameter (1.5m) Attached Inflatable Decelerators from Mach Numbers 2.2-4.4 1970 Originally recorded in 16mm, Silent, Color, 160ft., 4.5min. Deployment and Stability of Flexible Gliders 1960 16mm, Silent, Black & White, 360ft., 10min. Deployment Tests of the Stratos-Western Version of the Integrated Aircrew Escape/Rescue Capability (AERCAB) System in the Langley Full Scale Tunnel 1970 16mm, Silent, Black & White, 1010ft., 28min. Deployment Tests of Jinivik Air Cushion Recovery and Take Off Systems at High Forward Speeds 1977 16mm, Silent, Color, 1200ft., 28min. Development of a Towed-Model Flutter Test Technique in the Langley 19' Pressure Tunnel 16mm, Silent, Black & White Development of Ventilation on a Surface Piercing Hydrofoil 1958 16mm, Silent, Color, 100ft., 3min. Device Designed and Constructed at Langley Research Center Undergoing an Ejection and Inflation Test in the 5-by-10 Foot Vacuum Chamber. 1962 16mm, Silent, Black & White, 110ft., 3min. Direct Viewing Camera Records of TV Viewing Tests Conducted for Big Shot Program at LRC, March 16, 1961 (reel no. 1) and TV scope records of TV Viewing Tests Conducted for Big Shot Program at LRC, March 16, 1961 1961 Originally recorded in 16mm, Silent, Black & White, 150ft., 4min. Direct Viewing Camera Records of TV Viewing Tests Conducted for Big Shot Program at LRC, March16, 1961 (Reel no. 1) and TV Scope Records of TV Viewing Tests Conducted for Big Shot Program at LRC, March 16, 1961 (Reel no. 2) 1961 16mm, Silent, Black & White, 290ft., 8min. Ditching - A-26 (Part 2) 16mm, Silent, Black & White Ditching A 20-A Catapult 16mm, Silent, Black & White Ditching tests were made at the outdoor ditching catapult on a 1/10-scale model of the army A-20A airplane with full-scale weight of 17, 400 lbs. and flaps semi-fixed in the down position. Power off; high, medium, and low attitude; landings were made in smooth water and along the waves with the bomb-bay doors, the bombardier's sighting window, and the rear gun hatch removed since it was assumed that they would fail in full-scale ditchings. The model, of wooden construction, was ditched at angles of attack of 13-degrees, 9-degrees, and 4-degrees; and at airspeeds of 88, 102, and 118 MPH. Ditching-- A-20, B-26, B-25, B-17 16mm Ditching A-26 (Part III) 16mm, Silent, Black & White Ditching and Hydro-Ski Landing Tests of a 1/10-Scale Model of the Chance Vought Regulus I Missile 1957 16mm, Silent, Black & White, 250ft., 7min. Ditching B-24 with Eagle Ant. 16mm, Silent, Black & White Ditching tests were made on a 1/16-scale model of the Army B-24 airplane equipped with an Eagle antenna. The nose window, nose-wheel doors, bomb-bay doors, belly turret, and rear entrance hatch were removed to simulate their failure. The model was ditched with and without the antenna installed and dived each time. Tests were run at attitude angles of 9-degrees (tail down) and 1-degree (near level) and speeds of 100 and 120 MPH (full-scale). Ditching B-24 with Parachutes 16mm, Silent, Black & White Ditching tests were made in Tank #2 on a 1/16-scale model of the Army B-24 airplane equipped with tow 1/16 scale 24-ft. parachutes, attached to the leading edge of the wing at the root chord and at each waist-gun window. The nose window, nose-wheel doors, belly turret and rear entrance hatch were removed to simulate their failure. The model was launched from 1, 6, and 10 in. above the water at launching attitudes of 9-degrees (tail down) and 1-degree (near level); and speeds of 100 and 120 MPH (full-Scale). The parachutes opened over and under the horizontal tail. Ditching Boeing B-47 16mm, Silent, Black & White Ditching- Calm Water B-24 and B-17 Calm water ditching tests of Y16-size models of the Army B-24 & B-17 in Tank No. 2 16mm Ditching Chance Vought F7U-3 Part-3 16mm Ditching- Convair Liner- Part 1 16mm, Silent, Black & White Ditching- D-36, Part II 1947 Ditching tests of a1/20-scale model of the Army B-36 airplane. 16mm, Silent, Black & White Ditching Grumman F9F-2 Airplane--Part 1 16mm, Silent, Black & White Ditching Investigation Douglas C-124 (Film for Report 1347) 16mm, Silent, Black & White Ditching Investigation of a 0.043-Scale Model of the Boeing Jet Transport--Part I 16mm, Silent, Black & White, 125ft., 3min. Ditching Investigation of a 1/20-Scale Model of Space Shuttle Orbiter 1975 16mm, 390ft., 10.5min. Ditching Investigation of a 1/25-Scale Model of the Douglas YC-133 Airplane Part 1 16mm, Silent, Black & White, 170ft., 7min. Ditching Investigation of a 1/30-Scale Dynamic Model of a Heavy Jet Transport Airplane 1971 16mm, Silent, Color Ditching Investigation of a Dynamic Model of a HU2K-1 Helicopter 1961 16mm, Silent, Color, 165ft., 5min. Ditching Investigation of a Jet Transport with Various Engine Installations 1956 16mm, Silent, Black & White, 230ft., 9.5min. Ditching Model North American B-45 16mm Ditching-- Northrop C-125 Airplane- Part 1 16mm, Silent, Black & White Ditching of 1/12-Scale Model of the F3D-2--Part I. 16mm Ditching Preformance in the Army B-26 Plane 16mm, Silent, Black & White Ditching tests were made using the seaway catapult at Langley Field, VA., on a 1/12-scale dynamic model of the B-26 airplane in an over-load weight condition and a Half-fuel, no bomb-load condition; with flaps fixed in the down position. High, medium, and low attitude landings were made in smooth water; across waves, into wind; across wind, along waves; at airspeeds ranging from 110 to 145 MPH, weights of 26,200 and 35,000 lbs., and at attitude angles ranging from 13-degrees to 4-degrees. Ditching Test of a 1/10-Scale Model of the North American XFJ-1 Model 243 16mm Ditching tests of a 1/10-scale model of the North American FJ-1 airplane were made in calm water at the Tank #2 monorail to determine the effect of landing attitude in landing flaps, and damage on the ditching behavior of the airplane. Scale strength flaps were used and all values, including weight of 12,151 lbs. and C.G. at 162.15 in. aft of station 0 and 11.12 in. below the fuselage reference line, were full scale. Tests were made with no damage simulates; with the nose-wheel door dented and crumpled. Skipping caused by the curvature of the underside of the fuselage, was noticeable at all conditions but was most violent in the undamaged condition. Attitude angles were 12-degrees, 8-degrees, and 2-degrees; flap deflections were 0-degrees and 40-degrees; and speeds were 93.9, 104.3, 118.2, and 128.7 knots. The landing flaps always failed and had no detrimental effect on the ditching behavior; therefore, most tests were made with the flaps extended at 40-degrees. The preferred attitude for ditching was found to be 12-degrees. Ditching Tests Douglass DC-4 and DC-6 Part 1 16mm, Silent, Black & White Ditching Tests Lockheed Constellation Airplane with Speedpak Attached- Part 2 16mm, Silent, Black & White Ditching tests were made in Tank #2 on a 1/18-scale model of the Constellation with Speedpak attached. Tests were made in calm water at various attitudes, ranging from 4-degrees to 12-degrees, and flaps up or down and speeds ranging from 90 to 147 mph. The model is in the undamaged condition and scale-strength connections are used to attach the damaged Speedpak. Tests are also made with a scale-strength Speedpak attached. Ditching Tests Lockheed Constellation 16mm, Silent, Black & White Ditching tests were made in Tank # 2 on a 1/18-scale model of the Lockheed Constellation in calm water at landing attitudes ranging from 4-degrees to 12-degrees, with flaps both up and down and at speeds ranging from 85 to 171 mph. Tests were made on an undamaged model and on a model with scale strength bottom and landing gear doors removed. Ditching Tests Navy SB2C-1 (Pt. 1) 16mm, Silent, Black & White Ditching tests were made in calm water in Tank #2 on a 1/8-scale model of the Navy SB2C-1 airplane (Army A-25) to obtain effect of attitude, damage, flap setting and the effect of the arresting gear hook upon ditching. Gross Weight of the airplane was 12,060 lbs.; C.G. at 30.2% MAC and 1.2 in. below the thrust line auxiliary elevators, near the top of the rudder, were used to obtain the desired attitudes; spoilers were placed on the wing at all speeds above 78.2 knots to decrease the lift to the proper value; and scale strength flaps were used. Test doors, removed; and with bomb-sight doors and bomb-lever doors, bomb-bay doors, removed; and with bomb-sight doors and bomb-lever doors removed; at attitudes of 80-degrees (intermediate) and 15-degrees (tail down); speeds of 86.6, 78.2, 104.3, 112.9, 60.8, 95.6, and 69.6 knots; maximum longitudinal decelerations of 1.2, 1.3, 4.0, 1.4, 1.8, 7.6, 5.2, 4.8, 2.3, 7.4, 5.1, and 4.2 g; lengths of run from 2 to 26 times the fuselage length; with flaps full up, half down, and full down. The effect of the arresting gear was to cause the behavior of the model to change from skipping and porpoising to a violent drive. Ditching Tests Navy XP2V-1-- Part 1 16mm Ditching tests of a 1/16 Scale model of the Navy XP2V-1 airplane were made in calm water at the Langley Tank #2 monorail to determine the effect of landing attitude, position of the landing flaps, damage, and ditching aid on the ditching behavior of the airplane. Scale strength flaps were used and all values, weight, 45,000lb., C.G. at 29.3% MAC and 3.1 in. above thrust line; are full scale. Tests were made with no damage simulated to determine the effect of re-enforcing the bottom of the fuselage sufficiently to withstand the water loads of a ditching to determine the hydrodynamic effect of the landing flap. The bottom of the fuselage is unusually weak and so would be difficult to reinforce adequately. Tests were made with the nose-wheel doors, main-wheel doors, bomb-bay doors, radar turret, rear entrance door, and tow sections of the fuselage bottom aft of the bomb bays removed to simulate their failure. In this condition, the model dived. The simplest method of eliminating this diving would be the installation of a hydroflap under the forward party of the fuselage. When the hydroflap was located at the forward edge of the nose-wheel, door, the model continued to dive; but when it was relocated at the aft part of the nose-wheel, door, the diving was prevented. Tests were made attitude angles of 10-degrees, 6-degrees, and 2-degrees; with flaps up and full down; over a speed range from 71 to 211 knots. Ditching Tests of Chance Vought XF6U-Model P1 16mm, Silent, Black & White Ditching tests of a 1/8-scale model of the Vought XF6U-1 Airplane were made in calm water at the Langley Tank #2 monorail to determine the effect of landing attitude, landing flaps, and damage on the ditching behavior of the airplane. Scale strength flaps were used and all values, including weight of 9,706 lbs. and C.G. at 32.0% MAC and 5.75 in. above the thrust line, are full scale. runs were made with no damage simulated, to determine the behavior of the undamaged model and the effect of the landing flaps; with the engine access panel, engine removable pane, arresting gear door, main landing gear doors, fuel-pump access door, catapult doors, gun-access doors, and nose-wheel door removed to simulator their failure; and with engine access panel, and the engine removable panel, and the engine mounding system at approximately scale strength, to more accurately determine the amount of damage to be expected on the after fuselage, and the resulting motions. With the model in undamaged condition, the landing flaps always failed and had no detrimental effect on the ditching behavior, however violent trimming up and skipping was due to the shape of the aft portion of the fuselage. The attitude angles were 12-degrees, 8-degrees, and 4-degrees; flap deflection was 27-degrees; and speeds were 97.3, 106.9, and 123.3 knots. Pictures of the typical bottom damage at all attitudes were shown when tests were made with scale strength portions mentioned above. Ditching Tests of the Navy XR6O-1 Airplane 1947 16mm, Silent, Black & White Ditching tests were made in calm water at the Tank #2 monorail on a 1/24-scale model of the Navy XR6[Organizational Source] National Advisory Committee for Aeronautics, Langley Aeronautical Lab., Langley Field, VA.-1 airplane to determine the effect of landing attitude, position of land flaps, and damage. Scale strength flaps were used. Model tests with no simulated damage were used to determine the performance that would occur if the bottom could be adequately reinforced to prevent damage during ditching. Tests were also made with simulated failure of the nose-wheel doors and simulated crumpling aft of the nose-wheel doors. The scale-strength bottom was made of a light balsa framework covered with waterproof tissue paper, built to break under a uniformly distributed load of 5 pounds per square inch (full scale). Attitude range from 1-degree to 9-degrees, the flaps were full up or full down, and the speeds ranged from 91-132 MPH. Ditching Tests-North American F-86 16mm, Silent, Black & White Tests were made in calm water at the Tank #2 Monorail on a 1/10-scale model of the North American F-86 to determine the effect of Landing Attitude, landing flaps, and damage of the ditching behavior of the airplane. Scale-strength flaps were used and the first tests were made with no damage simulated. All tests were run at attitudes of 14-degrees, 9-degrees, and 4-degrees; with flaps at 0-degrees or 38-degrees; and at speeds ranging from 98 to 132 knots. The behavior at 14-degrees and 9-degrees; is considered satisfactory but the dive at 4-degrees is undesirable. The underside of the aft fuselage is weak enough is to incur some structural failure in calm-water ditching, so the next runs were made with the simulated crumpled bottom installed. At this condition, the runs were shorter, and the decelerations were higher. Next the empty 207 gallon wing fuel tanks were attached and runs made. The tanks seemed to suck the model under, so it is preferred that the wing-fuel tanks be jettisoned before a ditch is attempted. The results show that the preferred ditching conditions are 14-degrees attitude, flaps deflected 38-degrees and a speed of 98 knots. Ditching XC-123 Part 1 Ditching investigation of a 1/14-scale model of the XC-123 Airplane. 16mm, Silent, Black & White Divergence and Flutter Tests of 0.4-Scaled Model of the ASROC Rocket Motor Fins 1958 16mm, Silent, Black & White D-M 1 Part 4 1946 16mm, Silent, Black & White Smoke flow investigation was made in the full-scale tunnel over the wing of the DM-1 glider with and without sharp leading edges. Flow with the airplane in the original configuration passed over the center section in conventional manner with tip vortices of small extent being seen occasionally at CL of 0.57 and an angle of attack of 15.8-degrees. With a semi-span sharp leading edges installed a large vortex originated at the apex of the triangle and extended backward over the wing at CL of 0.6 and an angle of attack of 16.6-degrees. Documentary Film Report on Wind Tunnel Test of 1/12-Scale Model of Lockheed Polaris Missile 1958 16mm, Silent, Color 8.5min. Documentary of Environmental Testing of Project ECHO and Vibration Survey of MERCURY-ATLAS 1 1961 16mm, Silent, Color, 980ft., 13min. Dr. Theodorsens Flutter in 8 ft. H.S.T 16mm, Silent, Black & White Drag Characteristics of Several Towed Decelerator Models at Mach 3 1970 Originally recorded in 16mm, Silent, Black & White, 70ft., 2min. Drop Tests of a 1/30 Dynamically Scaled Model of the AVCO WS-107A Booster Vehicle From a Simulated Bomb Bay of a B-52 Airplane 16mm, Silent, Black & White, 170ft., 7min. Dynamic Analysis for Shuttle Design Verification 1972 16mm, Silent, Black & White, 4min. Dynamic Investigation of a Landing-Gear Configuration consisting of a Single Main Skid and a Nose Wheel 1960 16mm, Silent, Black & White, 250ft., 7min. Dynamic Model and Drogue Parachute Tests for 1/10-Scale Model of the NASA Manned Satellite in the Langley 20-Foot Free-Spinning Tunnel 1959 16mm, Silent, Black & White, 195ft., 8min. Dynamic Model Investigation of a 1/20 Scale Gemini Spacecraft in the Langley Spin Tunnel 1963 16mm, Silent, Black & White, 360ft., 18min. Dynamic Model Investigation of a 1/s0 Scale Gemini Spacecraft in the Langley Spin Tunnel 1963 Originally recorded in 16mm, Silent, Black & White, 360ft., 18min. Dynamic Model Investigation of Some Landings and Slideouts of Recoverable Booster 1966 16mm, Silent, Color, 75ft., 2min. Dynamic Model Investigation of the Landing Characteristics of a Manned Spacecraft 1964 Originally recorded in 16mm, Silent, Color, 215ft., 6min. Dynamic Model Investigation of the Rough Water Landing Characteristics of a Space Craft 1966 Originally recorded in 16mm, Silent, Color, 135ft., 3.5min. Dynamic Model Investigation of Water Pressures and Accelerations Encountered During Landings of the Apollo Spacecraft 1967 Originally recorded in 6mm, Silent, Color, 205ft., 5.7min. Dynamic Model Tests at Low Subsonic Speeds of Project Mercury Capsule Configurations with and without Drogue Parachutes 1960 16mm, Silent, Black & White, 300ft., 8.5min Dynamic Model Tests of Models in the McDonnell Design of Project Mercury Capsule in the Langley 20-Foot Free-Spinning Tunnel 1959 Originally recorded in 16mm, Silent, Black & White, 1285ft., 36min. Dynamic Model Tests of Models of the McDonnell Design of Project Mercury Capsule in the Langley 20-Foot Free-Spinning Tunnel 1961 16mm, Silent, Black & White, 800ft., 22min. Dynamic Model Tests of Project Mercury Capsules in the Langley 20-Foot Free-Spinning Tunnel 1959 16mm, silent, Black & White, 550ft., 15.5min. Dynamic Stability and Control Characteristics of a Cascade-Wing Vertically-Rising Airplane Model in Take-Offs, Landings, and Hovering Flight 1954 16mm Film, Silent, Black & White, 365ft., 10min. Dynamic Stability and Control Characteristics of a Ducted Fan Model in Hovering Flight 1954 16mm Film, Silent, Black & White, 230ft., 6.5min. Dynamic Stability Tests of Full-Scale Minneapolis Honeywell Hemosphere-Drogue Combinations in the Langley 20-Foot Vertical Wind Tunnel 1960 16mm, Silent, Black & White, 230ft., 6min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A 1958 16mm, Silent, Black & White, 175ft., 5min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A 1958 16mm, Silent, Black & White, 310ft., 8.5min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A 1985 16mm, Silent, Black & White, 150ft., 4min. Dynamic Store Release Tests in the Preflight Jet from a Model of the Lockheed F-104A. 1958 16mm, Silent, Black & White, 520ft., 14.5min. Dynamics of Anti-Skid Braking Systems 1982 16mm, Silent, Color, 600ft. Dynamics of Disk Galaxies 1969 16mm, Silent, Black & White, 205ft., 5.5min. Early Paraglider Tests 1962 16mm, Silent, Color, 12min Echo I 41-Foot Vacuum Sphere Ejection Tests 1965 16mm, Silent, Black & White, 485ft., 13.5min. Echo II 60-Foot Vacuum Chamber Sphere Ejection Tests 1965 16mm, Silent, Black & White, 323ft., 9min. Effect of Aerodynamic Heating on Flutter 1957 16mm, Silent, Black & White, 145ft., 4min. Effect of Chamber and L.E. on Unsteady Flows Past Thin Airfoils Mounted in 4""x19"" Tunnel. 16mm, Silent, Black & White Effect of Deflecting Ailerons with the Spin (Stick right in a Right Spin) on Recovery 16mm, Silent, Black & White, 190ft., 8min. Effect of Forward Protruding Nose Spikes on Blunt Shape Bodies at M=2.91 16mm, Silent, Black & White, 240ft., 6.5min. Effect of Gross Load Coefficient C [Delta Omega], on Bow Spray 16mm Effect of Gross Load Coefficient C^o, On Bow Spray 16mm Effect of Load-Alleviating Structure on the Landing Behavior of a Reentry-Capsule Model. 1961 Originally recorded in 16mm, Silent, Color, 77ft., 2min. Effects of the Atmospheric-Lithostatic Pressure Ration on Explosive Craters in Dry Soil 1971 16mm, Sound, Color, 25min. Effects of Wing Position and Vertical-Tail Configuration on Stability and Control Characteristics of a Jet-Powered Delta-Wing Vertically Rising Airplane Model. 1957 16mm, Silent, Black & White Ejection and Inflation Test in 41-foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 165ft., 12min. Ejection and Inflation Test in 41-foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 310ft., 8.5min. Ejection and Inflation Test in 41-foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 215ft., 6min. Ejection and Inflation Test in 41-Foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 315ft., 9min. Ejection and Inflation Test in Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 160ft., 4.5min. Ejection and Inflation Tests in 41-Foot Vacuum Chamber of Explorer 12-Foot Diameter Satellite 1958 16mm, Silent, Black & White, 175ft., 5min. Electra Model Investigation of Propeller Autoprecession 1961 16mm, Silent, Color, 320ft., 9min. Electric Arc Facilities 1962 16mm, Silent, Black & White, 240ft., 7min. Electron Beam Corner Flow Visualization 1967 16mm, Silent, Color, 77ft., 2.1min. Electron Beam Flow Visualization Studies on McDonnell-Douglas Aircraft Corp. Space Shuttle Concepts 1971 16mm, Silent, Color, 400ft. 11min. Elevated-Temperature Tests Under Static and Aerodynamic Conditions on Corrugated-Stiffened Panels 1959 16mm, Silent, Black & White, 450ft., 13min. Energy Efficient Flight (1974 Inspection Film) 1975 16mm, Sound, Color, 610ft., 17min. Erect and Inverted Parachute Recovery Tests of a 1/25-Scale Model of the Douglas F5D-1 Airplane 1956 16mm, Silent, Black & White, 320ft., 13min. Erect and Inverted Spin and Recovery Tests on the 1/40-Scale Model of the B-58 Airplane 1960 16mm, Silent, Black & White, 910ft., 25min. Erect Spin Tests of a 1/25-Scale Model of the Douglas F5D-1 Airplane 1955 16mm, Silent, Black & White, 760ft., 31min. Essex Carrier Smoke Flow 1945 16mm, silent, b/w Since a great deal of smoke was emitted from the guns on the Essex class aircraft carrier on firing, tests were run to determine which areas of the carrier were free from smoke so that fire stations could be set up in those areas, and therefore defense against enemy planes would be better since visibility would be clearer in those areas. The tests were made at airspeed of 1 MPH for all conditions and with deck guns pointing to bow, astern and broadside; with 5 in. turret guns parallel to the center line of the ship, to starboard, and to port; and angles of fire deck guns on port, high and low, and on starboard, high and low; at angles of yaw of the carrier of O, 30, 60, and 90 degrees to the right and left. Essex Carrier Smoke Flow 1945 16mm, Silent, Black & White Since a great deal of smoke was emitted from the guns on the Essex class aircraft carrier on firing, tests were run to determine which areas of the carrier were free from smoke so that fire stations could set up in those areas, and therefore defense against enemy plane could be better since visibility would be clearer in those areas. The tests were made at airspeed of 1MPH for all conditions and with deck guns pointing to bow, astern, and broadside; with 5 in. turret guns parallel to the center line of the ship, starboard, and to port; and angles of fire deck guns on port, high and low, and on starboard, high and low; at angles of yaw of the carrier of 0-degrees, 30-degrees, 60-degrees, and 90-degrees to the right and left. EVA Assembly of Large Space Structure Element 1981 Originally recorded in 16mm, Silent, Color, 25min. Evaluation of a Full-Scale Lunar Gravity Simulator comparsion of Landing-Impact Tests of a Full-Scale and a 1/6-Scale Model 1968 16mm, Silent, Color, 411ft., 11.5min. Evaluation of Gravity Simulation Technique for Studies of Man's Self of Locomotion in Lunar Environment 1963 16mm, Silent, Color, 315ft., 9min., Evolution of a Cylindrical Galaxy 16mm, Silent, Black & White Excerpt From Langley Research Center's XC-142 Terminal Area Flight Program-Nov 1968 to May 1970 1970 16mm, Silent, Color, 364ft.,10min. Excerpts from test Films Langley Impacting Structures Facility, Lunar Module 1968 Originally recorded in 16mm, Sound, Color, 105ft., 3min. Experimental Ablation Cooling 1958 Originally recorded in 16mm, 9 minutes, 330 feet, silent, b/w Experimental Ablation Cooling 1958 16mm, Silent, Black and White, 330ft., 9min. Experimental Design Studies and Flow Visualization of Proportional Laminar Flow Fluidic Amplifiers 1979 16mm, Sound, Color, 713ft., 26min. Experimental Ditching of a B-24 Airplane 16mm, Silent, Black & White, 924ft. Experimental Investigation of Aerodynamic Phenomena as Affected by Compressibility 16mm Experimental Investigation of Liquid Impact in a Model Propellant Tank 1965 16mm, Silent, color 185ft., 5min. Experimental Investigation of the Dynamic Stability and Controllability of a Towed M-2 Entry Vehicle Model 1964 16mm, Silent, Color, 375ft., 10min. Experimental Investigation of the Dynamic Stability of a Towed Parawing Glider Air Cargo Delivery System 1964 16mm, Silent, Color, 688ft., 19min. Experimental Investigation of the Dynamic Stability of Towed Parawing Glider Model 1962 16mm, Silent, Color 165ft., 4.5min. Experimental Investigation of the Landing Dynamics of Three Legged Spacecraft Models. 1974 16mm, Silent, Color, 4.5min. Experimental Research in Aerospace and Structural Dynamics 1964 16mm, Sound, Black & White, 590ft., 16.5min Experimental Studies of Rotational Fluid Sloshing 1961 16mm, Silent, Color, 490ft., 13min. Exploratory Investigation of Factors Affecting the Wing Tip Vortex 1972 16mm, Silent, Color, 638ft., 17.75min. Exploratory Study of Man's Self-Locomotion Capabilities with a Space Suit in Lunar Gravity 1964 16mm, Sound, Color, 360ft., 10min. Exploratory Study of Ventilated Flows About Yawed Surface -Piercing Struts 1959 16mm, Silent, Black & White, 200ft., 5min. Reported herein are the results of observations and measurements made in connection with a study of the phenomenon of the development of atmosphere-connected cavities about surface-piercing struts. Conditions for the existence of such ventilated flows which have been derived from the experimental data are presented. In addition, certain broad conclusions pertinent to model testing and full-scale design are reached. Further experimentation to define the inception of ventilation as a function of boundary-layer state or Reynolds number is required. Exploratory Tests of Several Cooling Schemes at High Stagnation Temperature 1957 16mm, Silent, Color, 200ft., 5.5min. Exploratory Wind Tunnel Investigation of Deployable Flexible Ventral Fins for Use as Emergency Spin Recovery Device 1971 16mm, silent, Color, 130ft., 3.5min. Explorer XII (S-3) Energetic Particles Satellite 1962 16mm, Sound, Color, 600ft., 17min. External Mixing Spray Gun Nozzle, Langley Innovations Film 1963 16mm, Sound, Color, 165ft., 4.5min. External Wing Fuel Tanks Used as Ditching Aids 1956 16mm, Silent, Black & White, 240ft., 10min. F.F.T. 16mm F.S.T Smoke Over Wing 16mm, 296ft. F.S.T. P-46 Tufts 16mm F.S.T. Smoke Over Transport Film No. F-105 Vapor Screen Test 16mm, Silent, Black & White, 60ft, 1.5min F2H-4 Radar Tracking Performed by VMF-L14 at MCAS, Cherry Point, N.C. for NACA, Langley Field, Va. 16mm, Silent, Black & White F-40-2677 1960 16mm, Silent, Color, Black & White, 413ft., 11.5min. F-40K Flight (Extra) Tuft studies of flow over horizontal and vertical tail surfaces of the Curtiss P-40K in flight are shown. 16mm F6F-Flutter Model 16mm F-8U Main Landing Gear Tests 1962 16mm, Silent, Color, 120ft., 3.5min. Fairchild C-82 Tests 1950 16mm, Silent, Black & White Tests were made in calm water in Tank #2 of a 1/15-scale model of the Fairchild C-82 airplane with landing flaps full down; with no damage simulated; with failure of nose-wheel doors, and aft cargo doors simulated; and with failure of nose-wheel, aft cargo doors, and paratainer hatch simulated; at attitude angles of 2-degrees, 7-degrees, and 12-degrees; over a full-scale speed range from 90 to 125 MPH. Of the three conditions of damage tested the last condition is most likely to occur in Full-scale ditchings. if this damage occurs, the cargo compartment will be a hazardous ditching station because of the rapid inrush of water. Fast Flight 1979 16mm, Silent, Color Fatigue Failures of Simple Panels Due to Intense Noise 16mm, Silent, Black & White, 100ft., 4min. Fatigue Film Cleveland Conference 1950 16mm, Silent, Black & White Fault Tolerant Multi Processor for Commercial Aircraft 16mm, 490ft., 13.5min. FFT Film to Accompany Paper ""Technique for Testing Models of VTOL and STOL Airplanes"" 1956 AGARD Meeting at Brussels, Belgium August 27 - 31, 1956 16mm, 20.5min FFT Hinged Tip Sequence Tech Film #18 16mm, Silent, Black & White Flight tests were made in the free-flight tunnel to determine the effect on lateral stability and control of fuel-carrying wing-tip extensions hinged so at to reduce the loads imposed on with structure. The wing-tip extensions of the model were ballasted to represent tips loaded with fuel and having about the same wing loading as the model without the tip extensions. With the tips fastened rigidly, the model flies more smoothly than the basic model because of the increased damping in roll and the higher moments of inertia. The higher moments of inertia, however, make it more difficult to control. with the tips hinged to the chordwise axis the model is more difficult to fly than when the tip are rigidly attached because of the erratic motions of the tips. The tip hinge axis skewed 20-degrees, the tip movement is reduced, but still large and the model does not fly well. The skew angle was increased to 45-degrees and although the amplitude of the tip motions were reduced, they were still objectionably large. Next tests were made with wing tips with 14% chord flaps linked to move up when the tip went up and down and the tip went down. The flaps were geared to give 20-degrees deflection for 1-degree tip deflections. These linked flaps, although theoretically only as effective as the 45-degree skewed hinge line, resulted in smaller tip motions and mad the model easier to fly. With a 20% chord flap and gearing increased to 3-degrees flap for 1-degree tip movement of the tips relative to the wing was virtually eliminated, and the model was easier to fly. FFT-Stability Control-- Tests Straight Wing Vertically Rising Airplane Take-Off, Landing, Hovering 16mm, Silent, Color Film of Free-Flight Tunnel Radio Control Activities 1956 16mm, Silent, Color, 430ft., 17min. Film on Computer Seminar 1968 16mm, Silent, Black & White Film Supplement to Low-Speed, Free-Flight Stability Test of a 1/10-Scale Model of the AVCO Reentry Shape 52 1957 16mm, Silent, Black & White, 44ft., 1.25min. Film Supplement to Paper Entitled ""Some Stability Problems of Vertically Rising Aircraft. 1955 16mm, Silent, Black & White, 422ft., 17min. Film Tests of Lockheed F-104 Model 16mm, Silent, Black & White, 100ft., 4min. Film to Accompany Paper Entitled Research on VTOL and STOL airplanes in the United States. Presented in Madrid Spain 1958 16mm, Silent, Color, 22.5min. Film to Accompany Talk Given by Charles H. Zimmerman to British Helicopter Society 1958 16mm, Silent, 280ft. Film Used at Meeting of High-Speed Aerodynamics Subcommittee. Wallops Island, Va, August 31, 1954. 1954 16mm, Silent, Color, 340ft., 14min. Film Used by Paul Hill in NACA Conference; November 1,2,3, 1955 1955 16mm, Silent, Color, 170ft., 7min. Fin Heating at High Stagnation Temperatures 16mm, Silent, Color, 560ft., 16min. Fire!! 16' Wind Tunnel 1950 This color film was made on Monday afternoon, Feb. 20, 1950 during the fire in which the tower on the 16-foot high-speed tunnel at Langley Laboratory burned. Firing Tests of Spherical Rocket Motors 1958 16mm, Silent, Color 750ft., 21min. First and Second Developmental Flight Test of Echo II (A-12) Spacecraft 1965 16mm, Silent, Black & White, 192ft., 5.5min. First Developmental Flight Test of A-2 Spacecraft 1962 Originally recorded in 16mm, Silent, Black & White First Flight of the F8-SCW 16mm, Silent, Color Five-Stage Hypersonic Flight Test in GE-PARD Ablation Investigation. Model no. H50-2842 1958 16mm, Silent, Color Five-Stage Hypersonic Free-Flight Research Vehicle 1958 16mm, Silent, Color 525ft., 14.5min. Flexible Wing Concept 1960 16mm, Silent, Color, 750ft., 21min. Flexible Wing Concept Made in 1961 1962 16mm, Silent, Color, 480ft., 15min. Flexible Wing Research and Development 1962 16mm, 380ft., 11min. Flight Demonstration of the Time Reference Scanning Beam Microwave Landing Systems 16mm, Sound, Color, 800ft., 22min. Flight Investigation of a V/STOL Transport Model Having Six Wing-Mounted Lift Fans 1971 16mm, Silent, Color, 220ft., 6min. Flight Investigation of a V/STOL transport Model With Four Pod-Mounted Lift Fans 1971 16mm, Silent, Color, 182ft., 5min. Flight Investigation of Dynamic Stability and Control Characteristics of a 1/10-Scale Model of a Variable Wing-Sweep Fighter Airplane Configuration 1967 16mm, Silent, Color, 305ft., 8.5min. Flight Investigation of Stability and Characteristics of a 1/4-Scale Model of a Tilt-Wing Vertical Take-off and Landing Aircraft 1957 16mm, Silient, Black & White, 665ft., 18min. An experimental investigation has been conducted to determine the dynamic stability and control characteristics of a tilt-wing vertical-take-off-and-landing aircraft with the use of a remotely controlled 1/4-scale free-flight model. The model had two propellers with hinged (flapping) blades mounted on the wing which could be tilted up to an incidence angle of nearly 90 deg for vertical take-off and landing. The investigation consisted of hovering flights in still air, vertical take-offs and landings, and slow constant-altitude transitions from hovering to forward flight. The stability and control characteristics of the model were generally satisfactory except for the following characteristics. In hovering flight, the model had an unstable pitching oscillation of relatively long period which the pilots were able to control without artificial stabilization but which could not be considered entirely satisfactory. At very low speeds and angles of wing incidence on the order of 70 deg, the model experienced large nose-up pitching moments which severely limited the allowable center-of-gravity range. Flight Investigation of Stability and Control characteristics of a 0.18-Scale Model of a Four Duct Tandem V/STOL Transport 1965 16mm, Silent, Color, 300ft., 8.5min. Flight Investigation of Stability and Control Characteristics of a 1/8-Scale Model of a Tilt-Wing Vertical Take-off and Landing Aircraft 1958 16mm, silent, Color, 1220ft., 34min. Flight Investigation of Stability and Control Characteristics of a 1/9-Scale Model of a Four Propeller Tilt-Wing V/Stol Transport 1964 16mm, Silent, Color, 625ft., 17min. Flight Investigation of the Dynamic Stability and Control Characteristics of a 0.18-Scale Model of a Fan-In-Wing VTOL Airplane. 1966 16mm, Silent, Color, 255ft., 7min. Flight Research with the Wing Flow Method 16mm, Silent, Color Flight Service Evaluation of PRD-49 Epoxy Panels on L-1011 Commercial Aircraft 1973 16mm, Sound, Color, 6.5min. Flight Test of 0.0565-Scale Martin Titan Heat Transfer Model 1957 16mm, Silent, Color, 385ft., 11min. Flight Test of 0.0565-Scale Martin Titan Heat Transfer Model 1957 16mm, Silent, Color, 115ft., 3min. Flight Test of 0.0565-Scale Martin Titan Heat Transfer Model 1958 16mm, Silent, Color, 62ft., 2min. Flight Test of 0.12-Scale Rocket-Boosted Model of NAVAHO II Model No.2 16mm, Silent, Black & White, 75ft, 3min Flight Test of 0.12-Scale Rocket-Boosted Model of NAVAHO II Model No.2 16mm, Silent, Color, 50ft, 2min Flight Test of 1/4-Scale Model No. 2 of Hermes A-3B Missile, Wallops Island, Va 1954 16mm, Silent, Black & White Flight Test of 31.2 Diameter Modified Ringsail Parachute Deployed at Mach 1.39, Dynamic Pressure 11 Pounds Per Square Foot 1967 Originally recorded in 16mm, Silent, Color, 120ft., 3.5min. Flight Test of a 0.12-Scale NAVAHO II Rocket Model 16mm, Silent, Color Flight Test of a 1/10-Scale Rocket-Powered Model of the Douglas XF4D-1 Airplane 16mm, Silent, Color, 95ft, 3.5min Flight Test of a 30-Foot Nominal Diameter Cross Parachute Deployed at Mach 1.57 and Dynamic Pressure of 9.7lbs/square ft 1968 Originally recorded in 16mm, Silent, Color, 120ft., 3.5min Flight Test of a 30-Foot Nominal-Diameter Disk-Gap-Band Parachute Deployed at Mach 1.56 and Dynamic Pressure of 11.4 Pounds Per Square Foot. 1967 Originally recorded in 16mm, Silent, Color 100ft., 3min. Flight Test of a 40-Foot Nominal Diameter Disk-Gap-Band Parachute Deployed at a Mach Number of 2.72 and a Dynamic Pressure of 9.7 Pounds Per Square Foot. 1968 Originally recorded in 16mm, Silent, Color, 111ft., 3min. Flight Test of a 40-Foot Nominal Diameter Disk-Gap-Band Parachute Deployed at a Mach Number of 3.31 and a Dynamic Pressure of 10.6 Pounds Per Square Foot. 1969 Originally recorded in 16mm, Silent, Color, 116ft., 3.2min. Flight Test of a 40-Foot Nominal-Diameter Disk-Gap-Band Parachute Deployed at a Mach Number of 1.91 and a Dynamic Pressure of 11.6 Pounds per Square Foot 1968 Originally recorded in 16mm, Silent, Color, 180ft., 5min. Flight Test of a Delta-Wing Jet-Powered Vertically Rising Airplane Model 1965 16mm, Silent, Color, 480ft., 13min. Flight Test of a0.13 Model of the Dornier D0-31 VTOL Airplane 1963 16mm, Silent, Color, 470ft., 13min. Flight Test of Bull Pup Missile at Wallops Island, Va. 1956 16mm, Silent, Color, 286ft., 8min. Flight Test of Chance Vought XF8U-1 Rocket Model No. 5 16mm, Silent, Color, 60ft, 2.5min Flight Test of Model D117-2484 1958 16mm, Silent, Color, 13min. Flight Test of Nike-Cajun Sounding Rocket 1956 16mm, Silent, Color, 125ft., 3.5min. Flight Test of the 7.5 Percent Scale Rocket-Boosted Model of the Martin WS-302A at Wallops Island, Va. 35mm, Silent, Black & White Flight Tests and Tuft Tests of 1/8-Scale Model of Bell D188A Jet VTOL Airplane in the Conventional Flight Condition 1958 16mm, Silent, Black & White Flight Tests in the Langley Full-Scale Tunnel of a 1-7 Scale-Model of the North American X-15 Airplane. 1958 16mm, Silent, Black & White, 605ft. 17min. Flight Tests in the Langley Full-Scale Tunnel of a Model with Horizontal Tail Used for Roll Control 1957 16mm, Silent, Black & White, 357ft., 10min. Flight Tests of ""TART"" Missile at the Pilotless Aircraft Research Station, Wallops, Va 1958 16mm, Silent, Color Flight Tests of 0.13-Scale Model Convair XFY-1 Vertical Rising Airplane Lower Vertical Tail Removed 16mm, Silent, Color Flight Tests of a 0.13-Scale Model of the Convair XFY-1 in Set-Up Simulating Proposal for Captive Flight Tests in a Hanger (Supplement to RM-SL54B16a). 16mm, Silent, Black & White Flight Tests of a 0.4-Scale Model of Stand-On Type Vertically Rising Aircraft 1954 16mm, Silent, Black & White, 320ft., 9min. Flight Tests of a 1/6-Scale Model of the Hawker P 1127 Jet VTOL Airplane 1961 16mm, Silent, Black & White, 14min. Flight Tests of a 1/8-Scale Model of the Bell D-188A Jet VTOL Airplane. TED No. AD 3147 1958 16mm, Silent, Black & White Flight Tests of a 40-Foot Nominal Diameter Modified Ringsail Parachute Deployed at Mach 1.64 and Dynamic Pressure of 91 Pounds Per Square Foot 1967 Originally recorded in 16mm, Silent, Color, 120ft., 3.3min. Flight Tests of a Model of a High Wing Transport VTO Airplane with Tilting Wing and Propellers and with Jet Controls at the Rear of the Fuselage for Pitch and Yaw Control 16mm, Silent, Color, An investigation of the stability and control of a high-wing transport vertical-take-off airplane with four engines during constant-altitude transitions from hovering to normal forward flight was conducted with a remotely controlled free-flight model. The model had four propellers distributed along the wing with the thrust axes in the wing chord plane. The wing could be rotated to 90 degrees incidence so that the propeller thrust axes were vertical for hovering flight. An air jet at the rear of the fuselage provided pitch and yaw control for hovering and low-speed flight. Flight Tests of a Model Similar to the F8U-1 Airplane in the Langley Full-Scale Tunnel 1956 16mm, Silent, Black & White, 250ft., 10min. Flight Tests of a Model Similar to the F8U-1 Airplane in the Langley Full-Scale Tunnel 16mm, Silent, Color, 75ft., 3min. Flight Tests of a Vertically Rising Airplane Research Model Interchangeable Swept and Unswept 16mm, Silent, Black & White Flight Tests of Ducted Rocket with Conical Shock Nose Inlet 1958 16mm, Silent, Color Flight Tests of the 1/5 - Scale Boeing Dyna-Soar Model (2002) in the Langley Full-Scale Tunnel 1960 16mm, Silent, Black & White, 1620ft., 45min. Flight Tests of the NACA Ram-Jet Test Vehicle Using Continental Aviation and Eng. Co. Solid Fuel 16mm, Silent, Color, 68ft, 2.34min Flight Tests of Three Arcon Rockets Fired from Wallops Island, Va. 1958 16mm, Silent, Color, 31min. Flight Tests Results from Supersonic Deployment of an 18-Foot Diameter (5.49 meter) Towed Ballute Decelerator 1969 Originally recorded in 16mm, Silent, Color, 112ft., 3min. Flights Clippings 16mm Flights of Ryan N14ON by Ryan Pilot at NASA Langley Research Center 1962 16mm, Silent, Color, 250ft., 7min. Flights of Two-Foot Gilding Parachute Made January 7, 1965 1965 16mm, Silent, Black & White, 150ft., 4min. Flow Behind Cylinder as Shown by Tuft Grid 16mm, Silent, Black & White, 100ft., 2.75min. Flow on the Surface OF the Wing by the Ink-Flow Visualization Method (Swept Wing and Straight Wing) 1957 16mm, Silent, Black & White, 175ft., 5min. Flow Over Blunt Body at M=20 in 2-Inch Helium Tunnel 1960 Originally recorded in 16mm, Silent, Black & White, 27ft., 1min. Flow Past Two Dimensional Air Foils in the Langley 4X19 inch Simi-open Tunnel as obtained by a Schlieren System (3 Reels) 16mm, Silent, Black & White, 2680ft., 72min. Flow Studies of Decelerators at Supersonic Speeds 1959 Originally recorded in 16mm, Silent, Black & White, 350ft., 10min. Flow Studies on a 49-Degree Swept-Wing Model with Trailing-Edge and Leading-Edge Blowing Applied. 16mm, Silent, Black & White, 80ft., 2min. Flow Visualization in Cascades and Rotors- E. Boxer, ASME Meeting of November 1960 1960 16mm, Silent, Color and Black & White, 215ft., 6min. Fluctuations in Supersonic Inlets 16mm, Silent, Black & White The phenomenon of flow fluctuation in supersonic inlets is investigated at the following subcritical conditions. Tests were made at Mach number 1.92 on an inlet having 30-degrees cone and 12 to 17-degrees cowling and no internal contraction. The Mach number at the cone surface is 1.20. The subcritical condition is stable until the boundary flow is supersonic at the jet boundary. The system of throttling is then changed and fluctuation phenomena is completely modified. Frequency and amplitude of fluctuation changed when tests were made at Mach number 1.92 on an inlet having 20-degrees cone and 13-17-degrees cowling and on internal contraction. The Mach number at the cone surface of 1.51 is too high. The subcritical condition is not stable and no regulation of volume flow is possible. The remaining tests were made at Mach number 2.70. No stable subcritical condition was possible for an inlet having 22-degrees cone and 4 to 7-degree cowl and internal contraction, when the Mach number at the cone surface was 2.02, an inlet having 40-degree cone and 16 to 24 degree cowl and Mach number at the surface 1.23 was tested. In the final test an inlet having gradual external compression and a low mach number at the surface at the entrance was tested, but subcritical conditions were not stable because of the existence of separation. Fluid Motion in a Simplified Tip Tank Model 16mm, Silent, Color Fluid Motion in a Simplified Tip Tank Model 16mm, Silent, Color Flutter at a Glance 1981 16mm, Sound, Color, 2.5min. Flutter 16mm, Silent, Black & White Presents short discussion of flutter and illustrations of the separate modes of vibration possible for a wing to execute. Tests were made in the NACA High-Speed Tunnel on both plastic and dural wing models at speeds up to 500 MPH. Of increasing importance is flutter involving all three vibrations; bending, torsion, and aileron motion about the hinge. Any two or all of these motions must be present simultaneously for flutter exist. Illustrations of each of these motions and combinations are presented. Flutter Film Which Accompanies the Presentation of the 1957 Minta Martin Lecture By Prof. T. E. Garrick 1958 16mm, Silent, Black & White Flutter Investigation in the Langley Transonic Blowdown Tunnel of Models of the F8U-3 Airplane Wing 1957 16mm, Silent, Black & White, 850ft., 23.5min Flutter Investigation of 1/15-Scale Models of A2F-1 Horizontal Tail Conducted in Langley Transonic Blowdown Tunnel 1959 16mm, Silent, Black & White, 290ft., 8min. Flutter Investigation of Canard Model of Beech XKD2B-1 Expendable Powered Target Conducted in Langley Transonic Blowdown Tunnel 1960 16mm, Silent, Black & White, 250ft., 7min. Flutter investigation of Parawing Models in the Langley Transonic Dynamics Tunnel 1961 Originally recorded in 16mm, Silent, Black & White, 405ft., 11.5min. Flutter Investigation of Simplified Models of Dyna-Soar 1 Booster Fins in the Langley Transonic Blowdown Tunnel 1961 16mm, Silent, Black & White, 7min. Flutter of a Large Variety of Models in the Langley Transonic Blowdown Tunnel 1962 16mm, Silent, Black & White, 250ft., 7min. Flutter of A Large Variety of models in the Langley Transonic Blowdown Tunnel Originally recorded in 16mm, Silent, Black & White Flutter of Buckled Curved and Flat panel at M=1.3 and 2.0 1965 16mm, Silent, Black & White, 86ft., 2.5min. Flutter TBF-1 16' W.T. 16mm, Silent, Black & White Flutter tests were made on a full-scale TBF-1 aileron installation in the 16 ft. high-speed tunnel. The model tested was an outer section of a production wing panel of the TBF-1 airplane. Aerodynamic tests were made of the wing-aileron installation to determine whether the aileron had contributed to the failures that have occurred in the service of the airplane. Flutter of this tests model occurred at airspeeds of about 150MPH. On the TBF-1 the wing panel is attached at 2 points at approximately 10 and 40% chord, therefore, the chordwise stiffness is low. Lacking chordwise rigidity, chordwise motion occurred. The C.G. of the aileron is forward of the hinge line, and therefore classical wing-aileron flutter was not possible. However, the method of attachment of the aileron to the wing panel places the C.G. 2.17 in. above the hinge line. The aileron is, therefore, deflected by inertia forces when chordwise motion and its attendant chordwise accelerations occur. Rearward motion of the wing therefore produces of negative aileron angle and forward motion of the wing a positive aileron angle. The alternation up and down aileron produces simple wing bending due to lift changes. No torsional deflection of the wing evident. In order to verify the fact that the chordwise motion was essential to flutter condition, the chordwise rigidity was greatly increased by the insertion of a steel block between the tunnel wall and wing at approximately 80% chord. Flutter did not occur of this test condition and maximum tests speed was 365 MPH. The results of this analysis indicate that flutter involving chordwise motion of the wing can be prevented by 2 methods: (1) By stiffening the wing attachment in the chordwise plane. (2) By mass-balancing the aileron in the normal-to-chord plane. Flutter Test of Fin-Rudder Model in Langley Transonic Blowdown Tunnel 1957 16mm, Silent, Black & White, 115ft., 3min. Flutter Test of Full Scale X-15 Vertical Tail in Langley 9X6 Foot Thermal Structures Tunnel 1958 16mm, Silent, Black & White, 250ft., 7min. Flutter Test of Horizontal-Tail Models of F8U-3 Airplane Test 334 1957 16mm, Silent, Black & White, 560ft., 15.5min. Flutter Tests in the Supersonic Flutter Apparatus, March 7 and 13, 1956 1956 16mm, Silent, Black & White, 300ft, 12min. Flutter Tests of a Model of the F-105B Airplane Horizontal Tail with Circular Yoke in the Langley 26-Inch Transonic Blowdown Tunnel Test 331 1957 16mm, Silent, Black & White, 2680ft., 74min. Flutter Tests of All Movable Horizontal Tails in the Langley Transonic Blow-Down Tunnel 16mm, Silent, Black & White, 290ft, 8min Flutter Tests of Beech XKD2B-1 Target Drone in the Langley 8-Ft. Transonic Pressure Tunnel 1960 16mm, Silent, Black & White, 836ft., 23min. Flutter Tests of Bell Outer-Wall Insulating Panel. NACA Supersonic Blowdown Jet, Gas Dynamics Laboratory 1957 16mm, Silent, Color, 190ft., 5min. Flutter Tests of Centaur Transition Panel in Unitary Plan Wind Tunnel 1961 16mm, Silent, Black & White, 240ft., 6.5min. Flutter Tests of Hysail Model in 2-Foot Transonic Aeroplasticity Tunnel 1959 16mm, Silent, Black & White, 250ft., 7min. Flutter Tests of Hysail Models in 4- by 4-Foot Supersonic Pressure Tunnel 1959 16mm, Silent, Black & White, 1285ft., 36min. Flutter Tests of Model of Navy P6M-1 Tail in Langley 26-Inch Transonic Blowdown Tunnel 16mm, Silent, Black & White, 50ft., 2min. Flutter Tests of Model of Navy P6M-1 Tail in Langley 26-Inch Transonic Blowdown Tunnel. Test 229 16mm, Silent, Black & White, 145ft., 8min. Flutter Tests of Models of the Horizontal Tail and Wing of the F8U-3 in the Langley 9- by 18- Inch Supersonic Flutter Tunnel 1957 16mm, Silent, Black & White, 1760ft., 48min. Flutter Tests of the 1/8-Scale Full Span Lockheed Electra in the Langley Transonic Dynamics Tunnel 1960 16mm, Silent, Black & White, 1210ft., 33.5min. Flutter Tests of X-15 Tail Surfaces in the Langley 9- by 18-Inch Supersonic Flutter Tunnel 1958 16mm, Silent, Black & White Flutter Tests of X-15 Tail Surfaces in the Langley 9-by 18-Inch Supersonic Flutter Tunnel 1957 16mm, Silent, Black & White, 242ft., 7min. Flutter Tests of XPB2M-1 16mm Flutter tests were made on a model of the Martin PBM-1 seaplane to determine if a low flutter speed exists because of the elastic coupling between wing and engine, the ultimate flutter speed, and the wing divergence speed. Certain structural weaknesses were disclosed by the tests. The model, made of the plastic pyrolin has characteristic speed ratio of 3.61. Flutter speed calculation gave a value of 98.5 MPH corresponding to 355.6 MPH for the original seaplane. The calculated divergence speed was 95 MPH and the divergence first appeared at 94 MPH. Tin this case, divergence speed is less than flutter speed so no flutter appeared. It was concluded that the torsion axis is too far rearward, particularly at the tip; and no low flutter velocity is introduced