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  • 1
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    Viscous shock-layer solutions with coupled radiation and ablation for earth entry (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 29; 173-181
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  • 2
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    Stagnation-point radiative heating relations for earth and Mars entries (1991)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Stagnation-point radiative heating rate expressions are presented for use in air and an approximate Martian atmosphere consisting of 97 percent CO2 and 3 percent N2. Thermochemical equilibrium is assumed throughout. The flight conditions and body dimensions that are modeled are representative of both manned and unmanned missions to Mars and return to earth. Comparisons between the heating rates computed using the expressions presented here and independent computations yielded maximum differences of about 20 to 30 percent.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Spacecraft and Rockets (ISSN 0022-4650); 28; 40-42
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  • 3
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    Equilibrium radiative heating tables for aerobraking in the Martian atmosphere (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Studies currently underway for Mars missions often envision the use of aerobraking for orbital capture at Mars. These missions generally involve blunt-nosed vehicles to dissipate the excess energy of the interplanetary transfer. Radiative heating may be of importance in these blunt-body flows because of the highly energetic shock layer around the blunt nose. In addition, the Martian atmosphere contains CO2, whose dissociation products are known to include strong radiators. An inviscid, equilibrium, stagnation point, radiation-coupled flow-field code has been developed for investigating blunt-body atmospheric entry. The method has been compared with ground-based and flight data for air, and reasonable agreement has been found. In the present work, the method was applied to a matrix of conditions in the Martian atmosphere. These conditions encompass most trajectories of interest for Mars exploration spacecraft. The predicted equilibrium radiative heating to the stagnation point of the vehicle is presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-102659 , NAS 1.15:102659
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  • 4
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    Equilibrium radiative heating tables for Earth entry (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The recent resurgence of interest in blunt-body atmospheric entry for applications such as aeroassisted orbital transfer and planetary return has engendered a corresponding revival of interest in radiative heating. Radiative heating may be of importance in these blunt-body flows because of the highly energetic shock layer around the blunt nose. Sutton developed an inviscid, stagnation point, radiation coupled flow field code for investigating blunt-body atmospheric entry. The method has been compared with ground-based and flight data, and reasonable agreement has been found. To provide information for entry body studies in support of lunar and Mars return scenarios of interest in the 1970's, the code was exercised over a matrix of Earth entry conditions. Recently, this matrix was extended slightly to reflect entry vehicle designs of current interest. Complete results are presented.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-102652 , NAS 1.15:102652
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  • 5
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    On optical imaging through aircraft turbulent boundary layers (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Optical resolution quality as affected by aircraft turbulent boundary layers is analyzed. Wind-tunnel data was analyzed to obtained the variation of boundary layer turbulence scale length and mass density rms fluctuations with Mach number. The data gave good agreement with a mass density fluctuation turbulence spectrum that is either isotropic of orthogonally anisotropic. The data did not match an isotropic turbulence velocity spectrum which causes an anisotropic non-orthogonal mass density fluctuation spectrum. The results indicate that the average mass density rms fluctuation is about 10% of the maximum mass density across the boundary layer and that the transverse turbulence scale size is about 10% of the boundary layer thickness. The results indicate that the effect of the turbulent boundary layer is large angle scattering which decreases contrast but not resolution. Using extinction as a criteria the range of acceptable aircraft operating conditions are given.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AMP-334 , NASA. Ames Res. Center Proc. of the Aero-Optics Symp. on Electromagnetic Wave Propagation from Aircraft; p 231-252
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  • 6
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    Air radiation revisited (1984)
    In:  Other Sources
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    Publication Date: 2019-06-28
    Description: The experimental data for air radiation from ground-based experiments and from the Fire II and Apollo 4 flights have been reviewed and compared with a single prediction method. The ground-based data agree generally with the trends predicted by the present calculations, but differences of a factor of two are noted. The flight data from Fire II and Apollo 4 are in good agreement with the present calculations with differences of less than 50 percent.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 84-1733
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  • 7
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    Relations for the thermodynamic and transport properties in the testing environment of the Langley hypersonic CF4 tunnel (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Thermodynamic and transport properties of gaseous CF4 that can be used in flow field computer codes and theoretical analyses for comparison of results with experimental data from the Langley Hypersonic CF4 Tunnel are presented. The thermodynamic relations which are based on thermally perfect but calorifically imperfect gas are adequate for the testing environment of the CF4 tunnel and are simpler to use than the imperfect gas relations required to define the complete expansion from the tunnel reservoir. Relations for the transport properties are based on the kinetic theory of gases in which published experimental data are used in the derivation of the relations. Extensive experimental data were located for viscosity and the derived relation should provide values for viscosity with errors of less than 1 percent. The experimental data for thermal conductivity were limited with significant disagreement between the various sources. The derived relation will probably provide values for the thermal conductivity with errors of no more than 5 percent which is within the accuracy of the experimental data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-TM-83220
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  • 8
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    Radiation absorption by the C2 band systems for Jupiter entry conditions (1979)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Revised values of the absorption cross sections for seven electronic band systems of C2 have been calculated using recently published experimental data for the electronic transition moments. Using these revised C2 cross section values, computations were made for the radiating flow field over a Jupiter entry probe with coupled ablation injection from a carbon-phenolic heat shield. Results are presented which show that radiation absorption within the ablation layer for the spectral range of 4 to 6 eV is less than that predicted using previous C2 absorption cross section values. The effect of the reduced radiation absorption by the C2 molecule is an increase in the radiative heating rates and ablation mass loss rates for the Jupiter entry conditions considered in the study.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 79-0033 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 15, 1979 - Jan 17, 1979; New Orleans, LA
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