Stagnation-point radiative heating relations for earth and Mars entries

Details Stagnation-point radiative heating relations for earth and Mars entries Stagnation-point radiative heating relations for earth and Mars entries

Feb 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991jspro..28...40t&link_type=abstract

Journal of Spacecraft and Rockets (ISSN 0022-4650), vol. 28, Jan.-Feb. 1991, p. 40-42.

Statistics

Computation

15

Atmospheric Entry, Earth Atmosphere, Mars Atmosphere, Radiant Heating, Reentry Vehicles, Stagnation Point, Atmospheric Composition, Chemical Equilibrium, Radiative Heat Transfer, Thermodynamic Equilibrium

Scientific paper

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.

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