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  • 1
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    Heating rate distributions at Mach 10 on a circular body earth-to-orbit transport vehicle (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A 0.0055-scale model of a single-stage-to-orbit transport vehicle with a circular body configuration was tested at Mach 10 to obtain heat transfer measurements and surface flow patterns. Phase-change paint and oil-flow tests were performed in the Langley 31-Inch Mach-10 Tunnel at angles of attack from 20 through 40 deg in 5-deg increments. Heat-transfer coefficient data are given for all angles of attack, and detailed oil-flow photographs are presented for windward and leeward surfaces at 25 and 40 deg angle of attack. Heating was found to similar to that previously determined for the Space Shuttle Orbiter, so that existing thermal protection systems would appear to be adequate for the proposed circular-body configurations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0974
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Wind-tunnel preflight test program for aeroassist flight experiment (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A proposed Aeroassist Flight Experiment (AFE) will simulate return from geosynchronous orbit to low-earth orbit to provide fundamental information about the hypersonic flow conditions surrounding aeroassisted orbital transfer vehicles (AOTV's). Future AOTV design must rely heavily on computational fluid dynamic (CFD) computer codes now under development, since the entry conditions are beyond the simulation capabilities of ground-based test facilities. However, existing codes and best available ground-based test facilities must provide for design of the AFE. The AFE ground-based test program provides data for calibration of existing and developing pertinent CFD codes. Confidence in code prediction capability increases with ability to predict forces and moments, pressure and heat-transfer distributions, shock shapes, and surface streamline directions. The ground-based test program provides these data over a wide range of hypersonic test parameters. This paper describes the test program, models, facilities, and some representative results.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 87-2367
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Measured and predicted aerodynamic coefficients and shock shapes for Aeroassist Flight Experiment (AFE) configuration (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two scaled models of the Aeroassist Flight Experiment (AFE) vehicle were tested in two air wind tunnels and one CF4 tunnel. The tests were to determine the static longitudinal aerodynamic characteristics, and shock shapes for the configuration in hypersonic continuum flow. The tests were conducted with a range of angle of attack to evaluate the effects of Mach number, Reynolds numbers, and normal shock density ratio.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2956 , L-16644 , NAS 1.60:2956
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wind-tunnel investigation of the aerodynamic pressures on the Apollo command module configuration (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Wind tunnel study of aerodynamic pressures on Apollo command module configuration
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-5514
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Measured and predicted aerodynamic heating on a cylinder in wake of AFE configuration at incidence (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Thin-film resistance gages were used to measure cylinder surface heat-transfer rates in the near wake of the Aeroassist Flight Experiment vehicle configuration, while surface-streamline directions were ascertained by the oil-flow techniques under the same configuration and test conditions. Both heat transfer distributions and flow over the entire cylinder surface were influenced by impingement of that portion of the free shear layer originating at the forebody shoulder in the upper symmetry plane. Heating rate distributions predicted with a Navier-Stokes solver computer code were in general agreement with measurements.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-2162 , AIAA Applied Aerodynamics Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, WA; United States
    Format: text
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    NASA TECHNICAL REPORTS
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