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  • 1
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    Benchmark determination of Shuttle Orbiter entry aerodynamic heat-transfer data (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 07, p. 965, Accession no. A82-19777
    Keywords: AERODYNAMICS
    Type: (ISSN 0022-4560)
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Shock-interaction-induced heat transfer to the orbiter wing lower surface (1985)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 22; 516-522
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Orbiter entry leeside heat-transfer data analysis (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Previously cited in issue 05, p. 586, Accession no. A83-16745
    Keywords: AERODYNAMICS
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 20; 524-530
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Computer graphic visualization of orbiter lower surface boundary-layer transition (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Computer graphic techniques are applied to the processing of Shuttle Orbiter flight data in order to create a visual presentation of the extent and movement of the boundary-layer transition front over the orbiter lower surface during entry. Flight-measured surface temperature-time histories define the onset and completion of the boundary-layer transition process at any measurement location. The locus of points which define the spatial position of the boundary-layer transition front on the orbiter planform is plotted at each discrete time for which flight data are available. Displaying these images sequentially in real-time results in an animated simulation of the in-flight boundary-layer transition process.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0228
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Analysis of entry aerodynamic heat-transfer data for the orbiter wing lower surface (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flight-derived aerodynamic heat-transfer data for the orbiter wing lower surface, from STS-2, -3, and -5, are presented and compared with both ground-based experimental results and state-of-the-art computational flowfield results for a nominal angle of attack of 40 degrees. The flight data clearly show the development of the interference heat-transfer region on the wing lower surface resulting from the downstream effects of the bow-shock/wing-shock interaction. The location of the interference heating region is well correlated with a region of minimum static enthalpy near the boundary-layer edge as predicted by a 3-dimensional, inviscid flowfield computation. The magnitude of the interference heat transfer is no greater than the undisturbed laminar heat transfer which occurs during the 'peak aerodynamic heating' portion of entry.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0227
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    NASA TECHNICAL REPORTS
  • 6
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    Influence of radiant energy exchange on the determination of convective heat transfer rates to Orbiter leeside surfaces during entry (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Temperatures measured at the aerodynamic surface of the Orbiter's thermal protection system (TPS), and calorimeter measurements, are used to determine heating rates to the TPS surface during atmospheric entry. On the Orbiter leeside, where convective heating rates are low, it is possible that a significant portion of the total energy input may result from solar radiation, and for the wing, cross radiation from the hot (relatively) Orbiter fuselage. In order to account for the potential impact of these sources, values of solar- and cross-radiation heat transfer are computed, based upon vehicle trajectory and attitude information and measured surface temperatures. Leeside heat-transfer data from the STS-2 mission are presented, and the significance of solar radiation and fuselage-to-wing cross-radiation contributions to total energy input to Orbiter leeside surfaces is assessed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0824 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
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    NASA TECHNICAL REPORTS
  • 7
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    Benchmark aerodynamic heat-transfer data from the first flight of the Space Shuttle Orbiter (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Benchmark entry aerodynamic heat-transfer data were determined from the first flight of the Space Shuttle Orbiter. The convective heating-rate data result from a rigorous mathematical analysis of one-dimensional, transient heat conduction within the orbiter thermal protection system (TPS) and reradiation from its surface during entry. Temperatures measured at the TPS surface during orbiter entry provide a constraint to the analysis. On the vehicle leeside, where heating rate levels are low, corrections are made to the computed convective heating rates to account for solar radiation and cross-radiation between fuselage and wing surfaces. The source of the entry thermal data, the mathematical analysis technique, and the TPS thermal models are discussed. Typical convective heating rate data from the STS-1 mission are presented.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0003 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
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    NASA TECHNICAL REPORTS
  • 8
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    Research analysis of Space Shuttle Orbiter entry aerothermodynamic flight data at the NASA Langley Research Center (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The methods used to analyze the aerothermodynamic data gathered from the Shuttle protoflights are reviewed. Trajectory and atmospheric reconstruction allow an accurate definition of the freestream environment through which the Shuttle has flown. The reconstructions, combined with aerodynamic coefficient and convective heating rate determinations, provide predictive capability for comparison with future flights. Data are acquired by operational instrumentation (12,000 parameters), development flight instrumentation (4500 measurements), and Orbiter experiments instrumentation; tracking and meteorological data are also included in the analyses. The aerothermodynamic and aerodynamic technology base for large, winged, lifting body entry vehicles is being expanded by the analysis efforts. Sensor locations on the Shuttle and data management techniques are described.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 81-2429 , Flight Testing Conference; Nov 11, 1981 - Nov 13, 1981; Las Vegas, NV
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    NASA TECHNICAL REPORTS
  • 9
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    Orbiter entry leeside heat-transfer data analysis (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Heat-transfer data measured along the Space Shuttle Orbiter's leeward centerline and over the wing leeside surface during the STS-2 and STS-3 mission entries are presented. The flight data are compared with available wind-tunnel results. Flight heating levels are, in general, lower than those which are inferred from the wind-tunnel results. This result is apparently due to the flight leeside flowfield remaining laminar over a larger Reynolds number range than that of corresponding ground test results. The flight/wind-tunnel data comparisons confirm the adequacy of, and conservatism embodied in, the direct application of wind-tunnel data at flight conditions for the design of Orbiter leeside thermal protection.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-0484 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
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    NASA TECHNICAL REPORTS
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