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  • 1
    Publication Date: 2019-06-28
    Description: This paper describes the rationale for conducting the proposed radiation measurement in the afterbody region of the Aeroassist Flight Experiment (AFE) vehicle, the results of the calculations of expected radiation intensities performed to date, and the instrumentation for the measurement. The experiment, named the Afterbody Radiometry Experiment (ARE), is one of the experiments that will be carried on board the AFE vehicle. The paper collates the existing experimental data to show the possibility that there may be substantial radiative heating of the afterbody region of an Aeroassisted Space Transfer Vehicle, which necessitates an experiment of the kind proposed. Calculations of the radiative heating rate to the base of the AFE are, qualitatively, in fair agreement with previous experimental work, which indicated that the radiative heating of the base is about 5 percent of that at the stagnation point.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 91-1408
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  • 2
    Publication Date: 2019-06-28
    Description: A forthcoming NASA flight experiment is described that provides an opportunity to obtain a large base of radiometric data for high-altitude, high-velocity thermochemically nonequilibrated-flow conditions. As a preliminary to the design of a radiometer for this experiment, an approximate method for predicting both equilibrium and nonequilibrium radiative surface fluxes is described. Spectral results for one trajectory state, a velocity of 10 km/sec at an altitude of 85 km, are presented. These results are then used to develop some of the instrument parameters that will be needed for designing of the three genre of radiometers that are proposed for this experiment.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 85-0967
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  • 3
    Publication Date: 2019-07-13
    Description: The ablation of carbonaceous materials in a hydrogen-helium stream has been simulated using a charring materials ablator computer code. These results are compared with the first ablation data to be obtained from the Ames-NASA Giant Planet Pilot Facility. Test stream diagnostics and ablation effects on convective and radiative heat transfer are discussed since these parameters constitute important input data to the numerical simulation. Graphite ablation was predicted to within 10 to 20%, and carbon-phenolic somewhat less accurately.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 78-866 , Thermophysics and Heat Transfer Conference; May 24, 1978 - May 26, 1978; Palo Alto, CA
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  • 4
    Publication Date: 2019-07-13
    Description: This paper describes the aerothermal environment in the afterbody region of a blunt entry body. Recent ground-based experiments and computational predictions of the afterbody flow structure and radiation are presented. The similarity between the flowfield structures observed in the ground-based experiments and that obtained by calculation is encouraging. Approximate calculations of the radiative heating rate to the base are presented. Many of the phenomena associated with the expanding flow at the corner and the formation of the wake neck, however, are not well understood and require further study. A flight experiment is described that would use spectral and total measurements of the wake radiation as a nonintrusive diagnostic method to provide insight into the thermodynamic state of the wake gas.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 91-1408 , Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 6; p. 765-772.
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  • 5
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    In:  Other Sources
    Publication Date: 2019-07-13
    Description: Material response solutions for the forebody heat shield on the candidate 310-kg Galileo Probe are presented. A charring material ablation analysis predicts thermochemical surface recession, insulation thickness, and total required heat shield mass. Benchmark shock layer solutions provide the imposed entry heating environments on the ablating surface. Heat shield sizing results are given for a nominal entry into modeled nominal and cool-heavy Jovian atmospheres, and for two heat-shield property models. The nominally designed heat shield requires a mass of at least 126 kg and would require an additional 13 kg to survive entry into the less probable cool-heavy atmosphere. The material-property model with a 30% surface reflectance reduces these mass requirements by as much as 16%.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 81-1073 , Thermophysics Conference; Jun 23, 1981 - Jun 25, 1981; Palo Alto, CA
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  • 6
    Publication Date: 2019-07-13
    Description: Implicit methods developed by Beam and Warming (1978 and Briley and McDonald (1977) make it possible to overcome the hyperbolic stiffness of the conservative compressible Navier-Stokes equations in the fine wall region computational mesh for high Reynold's number flow. Certain difficulties related to the use of these methods could be overcome by employing an approach reported by Roe (1981). In the present investigation Roe's conceptual framework has been adopted for constructing globally conservative finite difference methods. A globally conservative upwind finite difference method (CSCM) consisting of both implicit interior point and boundary point equations is constructed from a new characteristics based flux difference splitting. It is found that the employed upwind eigenvector split scheme which combines fully coupled implicit interior point and boundary point approximations has the desired properties of robust stability and accuracy.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 82-0837 , Joint Thermophysics, Fluids, Plasma and Heat Transfer Conference; Jun 07, 1982 - Jun 11, 1982; St. Louis, MO
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