SCAN_02-01

02-01 AERODYNAMICS CHARACTERISTICS
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Wind Tunnel Testing of Powered Lift, All-Wing STOL Model
Document ID:
20080031117
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Collins, Scott W. (Northrop Grumman Corp.) Westra, Bryan W. (Northrop Grumman Corp.) Lin, John C. (NASA Langley Research Center) Jones, Gregory S. (NASA Langley Research Center) Zeune, Cal H. (Air Force Research Lab.)
Published:
20080722
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
11
Contract #:
None
Abstract:
Short take-off and landing (STOL) systems can offer significant capabilities to warfighters and, for civil operators thriving on maximizing efficiencies they can improve airspace use while containing noise within airport environments. In order to provide data for next generation systems, a wind tunnel test of an all-wing cruise efficient, short take-off and landing (CE STOL) configuration was conducted in the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) 14- by 22-foot Subsonic Wind Tunnel. The test s purpose was to mature the aerodynamic aspects of an integrated powered lift system within an advanced mobility configuration capable of CE STOL. The full-span model made use of steady flap blowing and a lifting centerbody to achieve high lift coefficients. The test occurred during April through June of 2007 and included objectives for advancing the state-of-the-art of powered lift testing through gathering force and moment data, on-body pressure data, and off-body flow field measurements during automatically controlled blowing conditions. Data were obtained for variations in model configuration, angles of attack and sideslip, blowing coefficient, and height above ground. The database produced by this effort is being used to advance design techniques and computational tools for developing systems with integrated powered lift technologies.
Language:
English
Notes:
2008 International Powered Lift Conference London 22-24 Jul. 2008

Title:
Overview of CFD Validation Experiments for Circulation Control Applications at NASA
Document ID:
20080031119
Report #:
None
Available Online:
http://hdl.handle.net/2060/20080031119
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Jones, G. S. (NASA Langley Research Center) Lin, J. C. (NASA Langley Research Center) Allan, B. G. (NASA Langley Research Center) Milholen, W. E. (NASA Langley Research Center) Rumsey, C. L. (NASA Langley Research Center) Swanson, R. C. (NASA Langley Research Center)
Published:
20080722
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
16
Contract #:
None
Abstract:
Circulation control is a viable active flow control approach that can be used to meet the NASA Subsonic Fixed Wing project s Cruise Efficient Short Take Off and Landing goals. Currently, circulation control systems are primarily designed using empirical methods. However, large uncertainty in our ability to predict circulation control performance has led to the development of advanced CFD methods. This paper provides an overview of a systematic approach to developing CFD tools for basic and advanced circulation control applications. This four-step approach includes "Unit", "Benchmar", "Subsystem", and "Complete System" experiments. The paper emphasizes the ongoing and planned 2-D and 3-D physics orientated experiments with corresponding CFD efforts. Sample data are used to highlight the challenges involved in conducting circulation control computations and experiments.
Language:
English
Notes:
2008 International Powered Lift Conference London 22-24 Jul. 2008

02-02 AERODYNAMICS OF BODIES
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

02-03 AIRFOIL AND WING AERODYNAMICS
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

03-02 HELICOPTERS AND GROUND EFFECT MACHINES
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Fatigue Crack Growth Threshold Testing of Metallic Rotorcraft Materials
Document ID:
20080031096
Report #:
NASA/TM-2008-215331, ARL-TR-4472, L-19489
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Newman, John A. (NASA Langley Research Center) James, Mark A. (Alcoa Technical Center) Johnson, William M. (Lockheed Martin Engineering and Sciences Co.) Le, Dy D. (Army Research Lab.)
Published:
20080701
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
27
Contract #:
None
Abstract:
Results are presented for a program to determine the near-threshold fatigue crack growth behavior appropriate for metallic rotorcraft alloys. Four alloys, all commonly used in the manufacture of rotorcraft, were selected for study: Aluminum alloy 7050, 4340 steel, AZ91E Magnesium, and Titanium alloy Ti-6Al-4V (beta-STOA). The Federal Aviation Administration (FAA) sponsored this research to advance efforts to incorporate damage tolerance design and analysis as requirements for rotorcraft certification. Rotorcraft components are subjected to high cycle fatigue and are typically subjected to higher stresses and more stress cycles per flight hour than fixed-wing aircraft components. Fatigue lives of rotorcraft components are generally spent initiating small fatigue cracks that propagate slowly under near-threshold cracktip loading conditions. For these components, the fatigue life is very sensitive to the near-threshold characteristics of the material.
Language:
English

Title:
Flight Control Development for the ARH-70 Armed Reconnaissance Helicopter Program
Document ID:
20080031166
Report #:
None
Sales Agency:
Other Sources Copyright
Author(s):
Christensen, Kevin T. (Textron Bell Helicopter) Campbell, Kip G. (Textron Bell Helicopter) Griffith, Carl D. (Textron Bell Helicopter) Ivler, Christina M. (San Jose State Univ.) Tischler, Mark B. (San Jose State Univ.) Harding, Jeffrey W. (Harding Consulting, Inc.)
Published:
20080501
Source:
Textron Bell Helicopter (Fort Worth, TX, United States)
Pages:
19
Contract #:
None
Abstract:
In July 2005, Bell Helicopter won the U.S. Army's Armed Reconnaissance Helicopter competition to produce a replacement for the OH-58 Kiowa Warrior capable of performing the armed reconnaissance mission. To meet the U.S. Army requirement that the ARH-70A have Level 1 handling qualities for the scout rotorcraft mission task elements defined by ADS-33E-PRF, Bell equipped the aircraft with their generic automatic flight control system (AFCS). Under the constraints of the tight ARH-70A schedule, the development team used modem parameter identification and control law optimization techniques to optimize the AFCS gains to simultaneously meet multiple handling qualities design criteria. This paper will show how linear modeling, control law optimization, and simulation have been used to produce a Level 1 scout rotorcraft for the U.S. Army, while minimizing the amount of flight testing required for AFCS development and handling qualities evaluation of the ARH-70A.
Language:
English
Notes:
American Helicopter Society 63rd Annual Forum Virginia Beach, VA 1-3 May 2007

03-03 STOL AND VTOL AIRCRAFT
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

03-05 AIRCRAFT NOISE AND SONIC BOOM
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Vibroacoustic Response of Residential Housing due to Sonic Boom Exposure: A Summary of two Field Tests
Document ID:
20080031113
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Klos, Jacob (NASA Langley Research Center) Buehrle, Ralph (NASA Langley Research Center) Sullivan, Brenda (NASA Langley Research Center) Gavin, Joseph (Gulfstream Aerospace Corp.) Salamone, Joseph (Gulfstream Aerospace Corp.) Haering, Edward A., jr. (NASA Dryden Flight Research Center) Miller, Denise M. (Pennsylvania State Univ.)
Published:
20080728
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
12
Contract #:
None
Abstract:
Two experiments have been performed to measure the vibroacoustic response of houses exposed to sonic booms. In 2006, an old home in the base housing area of Edwards Air Force Base, built around 1960 and demolished in 2007, was instrumented with 288 transducers. During a 2007 follow-on test, a newer home in the base housing area, built in 1997, was instrumented with 112 transducers. For each experiment, accelerometers were placed on walls, windows and ceilings in bedrooms of the house to measure the vibration response of the structure. Microphones were placed outside and inside the house to measure the excitation field and resulting interior sound field. The vibroacoustic response of each house was measured for sonic boom amplitudes spanning from 2.4 to 96 Pa (0.05 to 2 lbf/sq ft). The boom amplitudes were systematically varied using a unique dive maneuver of an F/A-18 airplane. In total, the database for both houses contains vibroacoustic response data for 154 sonic booms. In addition, several tests were performed with mechanical shaker excitation of the structure to characterize the forced response of the houses. The purpose of this paper is to summarize all the data from these experiments that are available to the research community, and to compare and contrast the vibroacoustic behavior of these two dissimilar houses.
Language:
English
Notes:
Noise-Con 2008 Dearborn, MI 28-31 Jul. 2008

Title:
Measured Rattle Threshold of Residential House Windows
Document ID:
20080031114
Report #:
None
Available Online:
http://hdl.handle.net/2060/20080031114
Sales Agency:
CASI Hardcopy A02 No Copyright
Author(s):
Sizov, Natalia (Wyle Labs., Inc.) Schultz, Troy (Wyle Labs., Inc.) Hobbs, Christopher (Wyle Labs., Inc.) Klos, Jacob (NASA Langley Research Center)
Published:
20080728
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
9
Contract #:
NNL05AA04Z
Abstract:
Window rattle is a common indoor noise effect in houses exposed to low frequency noise from such sources as railroads, blast noise and sonic boom. Human perception of rattle can be negative that is a motivating factor of the current research effort to study sonic boom induced window rattle. A rattle study has been conducted on residential houses containing windows of different construction at a variety of geographic locations within the United States. Windows in these houses were excited by a portable, high-powered loudspeaker and enclosure specifically designed to be mounted on the house exterior to cover an entire window. Window vibration was measured with accelerometers placed on different window components. Reference microphones were also placed inside the house and inside of the loudspeaker box. Swept sine excitation was used to identify the vibration threshold at which the response of the structure becomes non-linear and begins to rattle. Initial results from this study are presented and discussed. Future efforts will continue to explore the rattle occurrence in windows of residential houses exposed to sonic booms.
Language:
English
Notes:
Noise-Con 2008 Dearborn, MI 28-31 Jul. 2008

03-06 AIRCRAFT SAFETY AND SAFETY DEVICES
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Space Vehicle Trajectory Monitoring in Real Time: Support to Decision Making for Flight Safety Group
Document ID:
20080031341
Report #:
INPE-14605-TDI/1185
Sales Agency:
CASI CD-ROM C01 Copyright
Author(s):
Louis, Joao Emile (Instituto de Pesquisas Espaciais)
Published:
20070101
Source:
Instituto de Pesquisas Espaciais (Sao Jose dos Campos, Brazil)
Pages:
153
Contract #:
None
Abstract:
Whenever satellites or scientific experiments are launched from vehicles, it is more than natural that the successful accomplishment of the mission is of interest to all the involved parties. In such activities, several teams with determined targets contribute as participating members. In terms of safety, the Flight Safety (SVO) team is responsible for protecting the public, internal and external to the operation. This group counts not only on pre-flight and post-flight information but also on the present status of the flight in order to conduct analysis. Information are constantly received from several tracking means such as radar and telemetry and they refer to the position of the vehicle. It is of fundamental importance to display such information in a proper way to the SVO as decisions such as aborting a flight, have to be made. Usually, launching centers are already equipped with tools to assist making such decisions. In order to contribute to the task of deciding on flight continuity, this dissertation proposes another method to conduct analysis of the trend of the actual trajectory. At each instant of the flight, a new trajectory calculation is conducted using the same facilities that predict a trajectory. This calculation occurs simultaneously with the flight and the characteristics of the vehicle and flight events are maintained as predicted. The only information received are duration of the flight and the vehicle position. Based on this information a new trajectory is determined and this results in a trajectory extrapolation obtained from the duration of the flight. These results enable the SVO to analyze not only the projection of the trend of the trajectory, but also the trajectory the vehicle should traverse, considering the initial conditions such as wind or any perturbation on leaving the launch pad. The results will be presented graphically by projecting the new determined trajectory on a computer monitor over a cartographic map. This display makes use of existing graphical tools for the internet known as open web standard technologies.
Language:
Portuguese

Title:
Laser Illumination of Aircraft by Geographic Location for a 3-Year Period (2004-2006)
Document ID:
20080031645
Report #:
DOT/FAA/AM-08/14
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Nakagawara, Van B. (Civil Aerospace Medical Inst.) Montgomery, Ron W. (Civil Aerospace Medical Inst.) Wood, Kathryn J. (Civil Aerospace Medical Inst.)
Published:
20080601
Source:
Civil Aerospace Medical Inst. (Oklahoma City, OK, United States)
Pages:
17
Contract #:
None
Abstract:
INTRODUCTION: Incidents involving laser illumination of aircraft in the National Airspace System have raised concerns within the aviation community for more than a decade. The principal concern is the visual effect laser illumination may have on flight crew performance during terminal operations, such as landing and departure maneuvers, when operational activities are extremely critical. This 3-year study examines the frequency and rate of aviation-related laser incidents by year and location. METHODS: Incident reports of civilian aircraft illuminated by high-intensity lights have been collected from various sources and entered into a database maintained by the Vision Research Team at the Civil Aerospace Medical Institute. Reported incidents of laser exposure of civilian aircraft in the United States for a 3-year period (January 1, 2004 to December 31, 2006) were collated and analyzed. RESULTS: A total of 832 incidents during the study period took place within the United States in the nine FAA-designated regions. For the period, total laser incident rates per 100,000 flight operations ranged from zero in the Alaskan region to 0.86 in the Western Pacific Region. Of the 202 airports where laser incidents occurred, there were 20 (9.9%) that reported 10 or more laser incidents during the study period. The majority of airports (52.6%) with 10 or more laser incidents reported a higher number of incidents in 2005 than in 2006. CONCLUSION: Laser illumination incidents that could compromise aviation safety and threaten flight crew vision performance occur with some regularity within the contiguous United States. While the study data indicate the Western Pacific Region had a significantly higher prevalence rate than the other FAA regions, analysis was complicated by incident clusters that occurred randomly at various airports. Actions taken by aviators, as well as local air traffic and law enforcement authorities that can minimize this threat to aviation safety, are discussed.
Language:
English

03-07 CLEAR AIR TURBULENCE
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Recent Insights into the Nature of Turbulence in the Solar Wind
Document ID:
20080031334
Report #:
None
Sales Agency:
Other Sources No Copyright
Author(s):
Goldstein, Melvun L. (NASA Goddard Space Flight Center)
Published:
20080511
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
1
Contract #:
None
Abstract:
During the past several years, studies of solar wind turbulence using data from Cluster and other spacecraft, and results from new numerical simulations, have revealed new aspects of solar wind turbulence. I will try to highlight some of that research. At the shortest length scales and highest frequencies, there is renewed interest in determining how the turbulence dissipates, e.g., whether by kinetic Alfven waves or whistler turbulence. Finding observational evidence for exponential damping of solar wind fluctuations has proven challenging. New studies using a combination of flux gate and search coil magnetometer data from Cluster have extended this search (in the spacecraft frame of reference) to more than 10 Hertz. New models and simulations are also being used to study the dissipation. A detailed study of fluctuations in the magnetosheath suggests that turbulent dissipation could be occurring at very thin current sheets as had been suggested by two-dimensional MHD simulations more than 20 years ago. Data from the four Cluster spacecraft, now at their maximum separation of 10,000 km provide new opportunities to investigate the symmetry properties, scale lengths, and the relative proportion of magnetic energy in parallel and perpendicular wave numbers of solar wind turbulence. By utilizing well-calibrated electron data, it has been possible to take advantage of the tetrahedral separation of Cluster in the solar wind near apogee to measure directly the compressibility and vorticity of the solar wind plasma.
Language:
English
Notes:
Dynamical Processes in Space Plasmas EN Boqeq, Dead Sea 11-19 May 2008

Title:
Stereoscopic Imaging in Hypersonics Boundary Layers using Planar Laser-Induced Fluorescence
Document ID:
20080031613
Report #:
AIAA 2008-4267
Available Online:
http://hdl.handle.net/2060/20080031613
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Danehy, Paul M. (NASA Langley Research Center) Bathel, Brett (Virginia Univ.) Inman, Jennifer A. (NASA Langley Research Center) Alderfer, David W. (NASA Langley Research Center) Jones, Stephen B. (NASA Langley Research Center)
Published:
20080623
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
14
Contract #:
None
Abstract:
Stereoscopic time-resolved visualization of three-dimensional structures in a hypersonic flow has been performed for the first time. Nitric Oxide (NO) was seeded into hypersonic boundary layer flows that were designed to transition from laminar to turbulent. A thick laser sheet illuminated and excited the NO, causing spatially-varying fluorescence. Two cameras in a stereoscopic configuration were used to image the fluorescence. The images were processed in a computer visualization environment to provide stereoscopic image pairs. Two methods were used to display these image pairs: a cross-eyed viewing method which can be viewed by naked eyes, and red/blue anaglyphs, which require viewing through red/blue glasses. The images visualized three-dimensional information that would be lost if conventional planar laser-induced fluorescence imaging had been used. Two model configurations were studied in NASA Langley Research Center's 31-Inch Mach 10 Air Wind tunnel. One model was a 10 degree half-angle wedge containing a small protuberance to force the flow to transition. The other model was a 1/3-scale, truncated Hyper-X forebody model with blowing through a series of holes to force the boundary layer flow to transition to turbulence. In the former case, low flowrates of pure NO seeded and marked the boundary layer fluid. In the latter, a trace concentration of NO was seeded into the injected N2 gas. The three-dimensional visualizations have an effective time resolution of about 500 ns, which is fast enough to freeze this hypersonic flow. The 512x512 resolution of the resulting images is much higher than high-speed laser-sheet scanning systems with similar time response, which typically measure 10-20 planes.
Language:
English
Notes:
38th AIAA Fluid Dynamics Conference and Exhibit Seattle, WA 23-26 Jun. 2008

Title:
Temperatures and Composition in the Saturn System from Cassini CIRS
Document ID:
20080031657
Report #:
None
Sales Agency:
Other Sources Copyright
Author(s):
Flasar, F. Michael (NASA Goddard Space Flight Center)
Published:
20080714
Source:
NASA Goddard Space Flight Center (Greenbelt, MD, United States)
Pages:
1
Contract #:
None
Abstract:
We summarize recent observations by the Composite Infrared Spectrometer of Saturn, its rings, Titan, and the icy satellites. Limb observations of Saturn show vertical oscillations of temperatures and zonal-wind shears in the equatorial region that may be related to a temporal oscillation similar to the terrestrial QBO and Jupiter's QQO. There is also evidence of subsidence at mid-northern latitudes driven by the equatorial activity. Nadir-viewing observations show compact warm spots in the troposphere and stratosphere at both (summer and winter) poles, likely associated with subsidence. Observations of Titan have defined better the characteristics of the northern winter polar vortex, with 190 m/s winds surrounding a cold atmosphere at 1 microbar. The very warm polar stratopause at 10 microbar and the enhanced abundances of organic compounds suggest subsidence within the vortex. Analysis of the zonal structure in temperature indicates that the stratospheric zonal winds rotate about an axis that is displaced approximately 4.1 deg from the IAU pole. Additional flybys, including a close one in March 2008, continue to characterize the endogenic activity in Enceladus s south polar region. Temperature maps of bright and dark terrains on Iapetus indicate that its ice is approximately stable to sublimation in the bright regions and highly unstable in the dark regions. Thermal mapping of Saturn s rings continues to constrain their composition, and observations at different solar phase angles, spacecraft elevations, solar elevations, and local hour angles have elucidated the effects of ring-particle shadowing and vertical motions on the thermal structure, and revealed the presence of small-scale structure associated with self-gravity wakes.
Language:
English
Notes:
COSPAR General Assembly Montreal 14-18 Jul. 2008

05-01 HYDRAULIC AND PNEUMATIC SYSTEMS
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

05-02 AUXILIARY ELECTRICAL SYSTEMS
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

No records are available for this topic on this date.

07-01 JET PROPULSION
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
The General Aviation Propulsion (GAP) Program
Document ID:
20080031112
Report #:
NASA/CR-2008-215266, E-16536
Available Online:
http://hdl.handle.net/2060/20080031112
Sales Agency:
CASI Hardcopy A04 No Copyright
Author(s):
(Author(s) Not Available)
Published:
20080701
Source:
Williams International (Walled Lake, MI, United States)
Pages:
65
Contract #:
NCC3-514
Abstract:
The General Aviation Propulsion (GAP) Program Turbine Engine Element focused on the development of an advanced small turbofan engine. Goals were good fuel consumption and thrust-to-weight ratio, and very low production cost. The resulting FJX-2 turbofan engine showed the potential to meet all of these goals. The development of the engine was carried through to proof of concept testing of a complete engine system. The proof of concept engine was ground tested at sea level and in altitude test chambers. A turboprop derivative was also sea-level tested.
Language:
English

Title:
Combustion Performance and Emissions Characteristics for a Well-Stirred Reactor for Low Volatility Hydrocarbon Fuels
Document ID:
20080031122
Report #:
AIAA Paper 2007-5663
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Stouffer, Scott D. (Dayton Univ. Research Inst.) Pawlik, Robert (Air Force Research Lab.) Justinger, Garth (Dayton Univ.) Heyne, Joshua (Dayton Univ.) Zelina, Joe (Air Force Research Lab.) Ballal, Dilip (Dayton Univ. Research Inst.)
Published:
20070708
Source:
NASA Johnson Space Center (Houston, TX, United States)
Pages:
12
Contract #:
NAS3-01135 200-18-14U38773
Abstract:
The performance and gaseous emissions were measured for a well-stirred reactor operating under lean conditions for two fuels: JP8 and a synthetic Fisher-Tropsch fuel over a range of equivalence ratios from 0.6 down to lean blowout. The lean blowout characteristics were determined in LBO experiments at loading parameter values from 0.7 to 1.4. The lean blowout characteristics were then explored under higher loading conditions by simulating higher altitude operation with the use of nitrogen to dilute the air. The results show that the two fuels have very similar combustion performance and lean blowout characteristics. Most of the differences observed in the emissions characteristics can be directly attributed to the difference in the C/H ratio of the two fuels.
Language:
English
Notes:
Paper is Appendix A of the original contractor report 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit Cincinnati, OH 8-11 Ju. 2007

09-01 WIND TUNNELS
Aug 31, 2008 -- Additions to the NASA scientific and technical information knowledge base

Title:
Unified Application Vapor Screen Flow Visualization and Pressure Sensitive Paint Measurement Techniques to Vortex- and Shock Wave-Dominated Flow Fields
Document ID:
20080031178
Report #:
ISFV13 Paper No. 122
Available Online:
http://hdl.handle.net/2060/20080031178
Sales Agency:
CASI Hardcopy A03 No Copyright
Author(s):
Erickson, Gary E. (NASA Langley Research Center)
Published:
20080701
Source:
NASA Langley Research Center (Hampton, VA, United States)
Pages:
31
Contract #:
None
Abstract:
Laser vapor screen (LVS) flow visualization and pressure sensitive paint (PSP) techniques were applied in a unified approach to wind tunnel testing of slender wing and missile configurations dominated by vortex flows and shock waves at subsonic, transonic, and supersonic speeds. The off-surface cross-flow patterns using the LVS technique were combined with global PSP surface static pressure mappings to characterize the leading-edge vortices and shock waves that coexist and interact at high angles of attack (alpha). The synthesis of LVS and PSP techniques was also effective in identifying the significant effects of passive surface porosity and the presence of vertical tail surfaces on the flow topologies. An overview is given of LVS and PSP applications in selected experiments on small-scale models of generic slender wing and missile configurations in the NASA Langley Research Center (NASA LaRC) Unitary Plan Wind Tunnel (UPWT) and 8-Foot Transonic Pressure Tunnel (8-Foot TPT).
Language:
English
Notes:
ISFV13 - 13th International Symposium on Flow Visualization FLUVISU12 - 12th French Congress on Visualization in Fluid Mechanics Nice Nice 1-4 Jul. 2008 1-4 Jul. 2008

Title:
An Experimental and Numerical Study of a Supersonic Burner for CFD Model Development
Document ID:
20080031179
Report #:
None
Sales Agency:
CASI Hardcopy A03 Copyright
Author(s):
Magnotti, G. (George Washington Univ.) Cutler, A. D. (George Washington Univ.)
Published:
20080720
Source:
George Washington Univ. (Newport News, VA, United States) NASA Langley Research Center (Hampton, VA, United States)
Pages:
14
Contract #:
None
Abstract:
A laboratory scale supersonic burner has been developed for validation of computational fluid dynamics models. Detailed numerical simulations were performed for the flow inside the combustor, and coupled with finite element thermal analysis to obtain more accurate outflow conditions. A database of nozzle exit profiles for a wide range of conditions of interest was generated to be used as boundary conditions for simulation of the external jet, or for validation of non-intrusive measurement techniques. A set of experiments was performed to validate the numerical results. In particular, temperature measurements obtained by using an infrared camera show that the computed heat transfer was larger than the measured value. Relaminarization in the convergent part of the nozzle was found to be responsible for this discrepancy, and further numerical simulations sustained this conclusion.
Language:
English
Notes:
44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit Hartford, CT 20-23 Jul. 2008