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  • 11
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    Hypersonic Nozzle/Afterbody Experiment: Flow Visualization and Boundary Layer Experiments (1994)
    In:  Other Sources
    Details
    Publication Date: 2019-07-17
    Description: This study was conducted to experimentally characterize the flow field created by the interaction of a single-expansion-ramp-nozzle (SERN) flow with a hypersonic external stream Data were obtained from a generic nozzle/afterbody model in the 3.5-Foot Hypersonic Wind Tunnel of the NASA Ames Research Center in a cooperative experimental program involving Ames and the McDonnell Douglas Aerospace. The model design and test planning were performed in close cooperation with members of the Ames computational fluid dynamics (CFD) team for the National Aero-Space Plane (NASP) program. This paper presents experimental results consisting of oil-flow and shadowgraph flow-visualization photographs, afterbody surface-pressure distributions, boundary-layer rake measurements, and Preston-tube skin-friction measurements.
    Keywords: Fluid Mechanics and Thermodynamics
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    Hypersonic single expansion ramp nozzle simulations (1992)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 749-755.
    Format: text
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    NASA TECHNICAL REPORTS
  • 13
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    Flowfield measurements about a multi-element airfoil at high Reynolds numbers (1993)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: This paper describes experimental data obtained with a multi-element airfoil at flight Reynolds numbers and lift coefficients including Clmax. The wind tunnel test was conducted in the NASA Langley Low Turbulence Pressure Tunnel as part of a cooperative effort between McDonnell Douglas Aerospace and NASA Langley. The airfoil model is a supercritical design configured with a leading-edge slat and a single-segment trailing-edge flap. Data include surface static-pressure distributions (integrated to obtain lift), drag data obtained with wake-rake surveys, and fbwfield surveys obtained with a flat-tube and five-hole probe at nine stations on the configuration's upper surface. Effects of variations in Reynolds number and flap gap on airfoil performance and flowfield survey data are presented.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-3137 , ; 16 p.|AIAA, Fluid Dynamics Conference; Jul 06, 1993 - Jul 09, 1993; Orlando, FL; United States
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    NASA TECHNICAL REPORTS
  • 14
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    Hypersonic nozzle/afterbody CFD code validation. I - Experimental measurements (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This study was conducted to obtain a detailed experimental description of the flow field created by the interaction of a single-expansion-ramp-nozzle flow with a hypersonic external stream. Data were obtained from a generic nozzle/afterbody model in the 3.5-Foot Hypersonic Wind Tunnel of the NASA Ames Research Center in a cooperative experimental program involving Ames and the McDonnell Douglas Research Laboratories. This paper presents experimental results consisting primarily of surveys obtained with a five-hole total-pressure/flow-direction probe and a total-temperature probe. These surveys were obtained in the flow field created by the interaction between the underexpanded jet plume and the external flow.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 93-0607 , ; 27 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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    NASA TECHNICAL REPORTS
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