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  • 1
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    Separate neural pathways for the visual analysis of object shape in perception and prehension (1994)
    Cell Press
    Details
    Publication Date: 1994-07-01
    Print ISSN: 0960-9822
    Electronic ISSN: 1879-0445
    Topics: Biology
    Published by Cell Press
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    PAPER CURRENT
  • 2
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    Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-to-Orbit Concepts (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: An overview of research efforts at NASA in support of the stage separation and ascent aerothermodynamics research program is presented. The objective of this work is to develop a synergistic suite of experimental, computational, and engineering tools and methods to apply to vehicle separation across the transonic to hypersonic speed regimes. Proximity testing of a generic bimese wing-body configuration is on-going in the transonic (Mach numbers 0.6, 1.05, and 1.1), supersonic (Mach numbers 2.3, 3.0, and 4.5) and hypersonic (Mach numbers 6 and 10) speed regimes in four wind tunnel facilities at the NASA Langley Research Center. An overset grid, Navier-Stokes flow solver has been enhanced and demonstrated on a matrix of proximity cases and on a dynamic separation simulation of the bimese configuration. Steady-state predictions with this solver were in excellent agreement with wind tunnel data at Mach 3 as were predictions via a Cartesian-grid Euler solver. Experimental and computational data have been used to evaluate multi-body enhancements to the widely-used Aerodynamic Preliminary Analysis System, an engineering methodology, and to develop a new software package, SepSim, for the simulation and visualization of vehicle motions in a stage separation scenario. Web-based software will be used for archiving information generated from this research program into a database accessible to the user community. Thus, a framework has been established to study stage separation problems using coordinated experimental, computational, and engineering tools.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2004-2595 , 24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference; 28 Jun. 1 Jul. 2004; Portland, OR; United States
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    NASA TECHNICAL REPORTS
  • 3
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    Aerodynamic Characteristics and Glide-Back Performance of Langley Glide-Back Booster (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: NASA-Langley Research Center is conducting system level studies on an-house concept of a small launch vehicle to address NASA's needs for rapid deployment of small payloads to Low Earth Orbit. The vehicle concept is a three-stage system with a reusable first stage and expendable upper stages. The reusable first stage booster, which glides back to launch site after staging around Mach 3 is named the Langley Glide-Back Booster (LGBB). This paper discusses the aerodynamic characteristics of the LGBB from subsonic to supersonic speeds, development of the aerodynamic database and application of this database to evaluate the glide back performance of the LGBB. The aerodynamic database was assembled using a combination of wind tunnel test data and engineering level analysis. The glide back performance of the LGBB was evaluated using a trajectory optimization code and subject to constraints on angle of attack, dynamic pressure and normal acceleration.
    Keywords: Launch Vehicles and Launch Operations
    Type: AIAA Paper 2004-5382 , 22nd AIAA Applied Aerodynamics Conference and Exhibit; Aug 16, 2004 - Aug 19, 2004; Providence, RI; United States
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    NASA TECHNICAL REPORTS
  • 4
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    X-33 Aerodynamic and Aeroheating Computations for Wind Tunnel and Flight Conditions (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This report provides an overview of hypersonic Computational Fluid Dynamics research conducted at the NASA Langley Research Center to support the Phase II development of the X-33 vehicle. The X-33, which is being developed by Lockheed-Martin in partnership with NASA, is an experimental Single-Stage-to-Orbit demonstrator that is intended to validate critical technologies for a full-scale Reusable Launch Vehicle. As part of the development of the X-33, CFD codes have been used to predict the aerodynamic and aeroheating characteristics of the vehicle. Laminar and turbulent predictions were generated for the X 33 vehicle using two finite- volume, Navier-Stokes solvers. Inviscid solutions were also generated with an Euler code. Computations were performed for Mach numbers of 4.0 to 10.0 at angles-of-attack from 10 deg to 48 deg with body flap deflections of 0, 10 and 20 deg. Comparisons between predictions and wind tunnel aerodynamic and aeroheating data are presented in this paper. Aeroheating and aerodynamic predictions for flight conditions are also presented.
    Keywords: Launch Vehicles and Launch Operations
    Type: AIAA Paper 99-4163 , AIAA Atmospheric Flight Mechanics Conference; Aug 09, 1999 - Aug 11, 1999; Portland, OR; United States
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    NASA TECHNICAL REPORTS
  • 5
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    X-33 Hypersonic Aerodynamic Characteristics (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Lockheed Martin Skunk Works, under a cooperative agreement with NASA, will build and fly the X-33, a half-scale prototype of a rocket-based, single-stage-to-orbit (SSTO), reusable launch vehicle (RLV). A 0.007-scale model of the X-33 604B0002G configuration was tested in four hypersonic facilities at the NASA Langley Research Center to examine vehicle stability and control characteristics and to populate an aerodynamic flight database i n the hypersonic regime. The vehicle was found to be longitudinally controllable with less than half of the total body flap deflection capability across the angle of attack range at both Mach 6 and Mach 10. At these Mach numbers, the vehicle also was shown to be longitudinally stable or neutrally stable for typical (greater than 20 degrees) hypersonic flight attitudes. This configuration was directionally unstable and the use of reaction control jets (RCS) will be necessary to control the vehicle at high angles of attack in the hypersonic flight regime. Mach number and real gas effects on longitudinal aerodynamics were shown to be small relative to X-33 control authority.
    Keywords: Avionics and Aircraft Instrumentation
    Type: AIAA Paper 99-4162 , AIAA Atmospheric Flight Mechanics Conference and Exhibit; Aug 09, 1999 - Aug 11, 1999; Portland, OR; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Supersonic Aerodynamic Characteristics of Proposed Mars '07 Smart Lander Configurations (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Supersonic aerodynamic data were obtained for proposed Mars '07 Smart Lander configurations in NASA Langley Research Center's Unitary Plan Wind Tunnel. The primary objective of this test program was to assess the supersonic aerodynamic characteristics of the baseline Smart Lander configuration with and without fixed shelf/tab control surfaces. Data were obtained over a Mach number range of 2.3 to 4.5, at a free stream Reynolds Number of 1 x 10(exp 6) based on body diameter. All configurations were run at angles of attack from -5 to 20 degrees and angles of sideslip of -5 to 5 degrees. These results were complemented with computational fluid dynamic (CFD) predictions to enhance the understanding of experimentally observed aerodynamic trends. Inviscid and viscous full model CFD solutions compared well with experimental results for the baseline and 3 shelf/tab configurations. Over the range tested, Mach number effects were shown to be small on vehicle aerodynamic characteristics. Based on the results from 3 different shelf/tab configurations, a fixed control surface appears to be a feasible concept for meeting aerodynamic performance metrics necessary to satisfy mission requirements.
    Keywords: Lunar and Planetary Science and Exploration
    Type: AIAA Paper 2002-4409 , AIAA Atmospheric Flight Mechanics Conference and Exhibit; Aug 05, 2002 - Aug 08, 2002; Monterey, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Testing of the Trim Tab Parametric Model in NASA Langley's Unitary Plan Wind Tunnel (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: In support of NASA's Entry, Descent, and Landing technology development efforts, testing of Langley's Trim Tab Parametric Models was conducted in Test Section 2 of NASA Langley's Unitary Plan Wind Tunnel. The objectives of these tests were to generate quantitative aerodynamic data and qualitative surface pressure data for experimental and computational validation and aerodynamic database development. Six component force-and-moment data were measured on 38 unique, blunt body trim tab configurations at Mach numbers of 2.5, 3.5, and 4.5, angles of attack from -4deg to +20deg, and angles of sideslip from 0deg to +8deg. Configuration parameters investigated in this study were forebody shape, tab area, tab cant angle, and tab aspect ratio. Pressure Sensitive Paint was used to provide qualitative surface pressure mapping for a subset of these flow and configuration variables. Over the range of parameters tested, the effects of varying tab area and tab cant angle were found to be much more significant than varying tab aspect ratio relative to key aerodynamic performance requirements. Qualitative surface pressure data supported the integrated aerodynamic data and provided information to aid in future analyses of localized phenomena for trim tab configurations.
    Keywords: Aerodynamics
    Type: NF1676L-15681 , AIAA Applied Aerodynamics Conference; Jun 24, 2013 - Jun 27, 2013; San Diego, CA; United States
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    NASA TECHNICAL REPORTS
  • 8
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    Orion Crew Module Aerodynamic Testing (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The Apollo-derived Orion Crew Exploration Vehicle (CEV), part of NASA s now-cancelled Constellation Program, has become the reference design for the new Multi-Purpose Crew Vehicle (MPCV). The MPCV will serve as the exploration vehicle for all near-term human space missions. A strategic wind-tunnel test program has been executed at numerous facilities throughout the country to support several phases of aerodynamic database development for the Orion spacecraft. This paper presents a summary of the experimental static aerodynamic data collected to-date for the Orion Crew Module (CM) capsule. The test program described herein involved personnel and resources from NASA Langley Research Center, NASA Ames Research Center, NASA Johnson Space Flight Center, Arnold Engineering and Development Center, Lockheed Martin Space Sciences, and Orbital Sciences. Data has been compiled from eight different wind tunnel tests in the CEV Aerosciences Program. Comparisons are made as appropriate to highlight effects of angle of attack, Mach number, Reynolds number, and model support system effects.
    Keywords: Aerodynamics
    Type: AIAA Papaer 2011-3502 , NF1676L-11731 , 29th AIAA Applied Aerodynamics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
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    NASA TECHNICAL REPORTS
  • 9
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    An Experimental Parametric Study of Geometric, Reynolds Number, and Ratio of Specific Heats Effects in Three-Dimensional Sidewall Compression Scramjet Inlets at Mach 6 (1993)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Since mission profiles for airbreathing hypersonic vehicles such as the National Aero-Space Plane include single-stage-to-orbit requirements, real gas effects may become important with respect to engine performance. The effects of the decrease in the ratio of specific heats have been investigated in generic three-dimensional sidewall compression scramjet inlets with leading-edge sweep angles of 30 and 70 degrees. The effects of a decrease in ratio of specific heats were seen by comparing data from two facilities in two test gases: in the Langley Mach 6 CF4 Tunnel in tetrafluoromethane (where gamma=1.22) and in the Langley 15-Inch Mach 6 Air Tunnel in perfect gas air (where gamma=1.4). In addition to the simulated real gas effects, the parametric effects of cowl position, contraction ratio, leading-edge sweep, and Reynolds number were investigated in the 15-Inch Mach 6 Air Tunnel. The models were instrumented with a total of 45 static pressure orifices distributed on the sidewalls and baseplate. Surface streamline patterns were examined via oil flow, and schlieren videos were made of the external flow field. The results of these tests have significant implications to ground based testing of inlets in facilities which do not operate at flight enthalpies.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 93-0740
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Orion Launch Abort Vehicle Attitude Control Motor Testing (2011)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Current Orion Launch Abort Vehicle (LAV) configurations use an eight-jet, solid-fueled Attitude Control Motor (ACM) to provide required vehicle control for all proposed abort trajectories. Due to the forward position of the ACM on the LAV, it is necessary to assess the effects of jet-interactions (JI) between the various ACM nozzle plumes and the external flow along the outside surfaces of the vehicle. These JI-induced changes in flight control characteristics must be accounted for in developing ACM operations and LAV flight characteristics. A test program to generate jet interaction aerodynamic increment data for multiple LAV configurations was conducted in the NASA Ames and NASA Langley Unitary Plan Wind Tunnels from August 2007 through December 2009. Using cold air as the simulant gas, powered subscale models were used to generate interaction data at subsonic, transonic, and supersonic test conditions. This paper presents an overview of the complete ACM JI experimental test program for Orion LAV configurations, highlighting ACM system modeling, nozzle scaling assumptions, experimental test techniques, and data reduction methodologies. Lessons learned are discussed, and sample jet interaction data are shown. These data, in conjunction with computational predictions, were used to create the ACM JI increments for all relevant flight databases.
    Keywords: Launch Vehicles and Launch Operations
    Type: AIAA Paper 2011-3343 , NF1676L-11717 , 29th AIAA Applied Aerodynamics Conference; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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