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  • 1
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    Heat-transfer testing procedures in phase B shuttle studies with emphasis on phase change data improvement (1972)
    In:  CASI
    Details
    Publication Date: 2006-07-18
    Description: The procedures used in the application of the phase change technique to the phase B shuttle configuration are discussed along with factors which may affect data accuracy. These factors include variation of thermal properties of phase change model material, sensitivity of measured heat transfer coefficients to the assumed value of the adiabatic to total temperature ratio, and wall temperature effects. These sensitivities are illustrated in sample calculations for a shuttle geometry. Factors which may affect the visual clarity and interpretation of phase change data are discussed, and a method of improving photographic data quality through the use of polarized light is presented.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Space Shuttle Aerothermodyn. Technol. Conf., vol. 2; p 661-682
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Comprehensive analysis of Shuttle Orbiter leeside surface infrared imagery obtained during atmospheric entry (1986)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The thermographic analysis techniques developed for processing of data from the Shuttle Infrared Leeside Temperature Sensing (SILTS) experiment are discussed. The SILTS experiment will obtain high-spatial-resolution infrared images of the leeside of the Space Shuttle Orbiter during atmospheric entry by means of a scanning infrared radiometer located atop the orbiter's vertical stabilizer. Comprehensive analysis of the SILTS thermography requires accurate consideration of all those factors (such as geometry of the observed surfaces, local surface emissivity, solar radiation, and other potential sources of image degradation) which may potentially affect the output of the infrared radiometer. An overview of the entire data processing procedure and brief descriptions of the data processing algorithms are presented.
    Keywords: SPACECRAFT INSTRUMENTATION
    Format: text
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  • 3
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    Aerodynamic heat transfer to RSI tile surfaces and gap intersections (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Review of the results of aerothermal heating tests of a simulated reusable surface insulation (RSI) tile array, performed on the sidewall of a Mach-10 hypersonic tunnel. In particular, the heating characteristics of the tile array, such as they result from heating inside the tile-expansion-space providing gaps between individual tiles, are investigated. The results include the finding that heating on the upstream face of a tile is strongly affected by the interacting longitudinal gap flow.
    Keywords: THERMODYNAMICS AND COMBUSTION
    Type: Journal of Spacecraft and Rockets; 11; June 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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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)
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  • 5
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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
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  • 6
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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
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  • 7
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    Orbiter catalytic/noncatalytic heat transfer as evidenced by heating to contaminated surfaces on STS-2 and STS-3 (1983)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: During that portion of Space Shuttle orbiter entry when significant aerodynamic heat transfer occurs, the flow over the vehicle is in chemical nonequilibrium. The parameter which most significantly influences the level of surface heat transfer in such a flow field is the catalytic efficiency of the surface with respect to the recombination of dissociated oxygen atoms. Significant, and instantaneous, changes were observed in the level of heat transfer at several lower surface centerline locations on STS-2 and STS-3. This phenomenon apparently resulted from a sudden change in the surface catalytic efficiency at these locations due to contamination of the surface by metallic oxides. As a result, data obtained from affected measurements cannot be considered as benchmark data with which to attempt to characterize nonequilibrium heat transfer to the orbiter's lower surface centerline.
    Keywords: SPACE TRANSPORTATION
    Type: Shuttle Performance: Lessons Learned, Pt. 2; p 847-864
    Format: application/pdf
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  • 8
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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
  • 9
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    Preliminary Analysis of STS-3 Entry Heat-Transfer Data for the Orbiter Windward Centerline (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A preliminary analysis of heat transfer data on the space shuttle orbiter windward centerline for the STS-3 mission entry is presented. Temperature-time history plots for each measurement location and tabulated wall temperature and convective heating rate data at 21 selected trajectory points are included. The STS-3 flight data are also compared with predictions by two approximation methods for computing convective heat transfer rates in equilibrium air.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-84500 , NAS 1.15:84500
    Format: application/pdf
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  • 10
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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
    Format: text
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