MEASUREMENTS OF HYPERVELOCITY STAGNATION POINT HEAT TRANSFER IN SIMULATED PLANETARY ATMOSPHERES
GENERAL ELECTRIC CO PHILADELPHIA PA MISSILE AND SPACE DIV
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The heat transfer to the stagnation region of a hemispherical body at flight velocities up to 40,000 ftsec in two CO2-N2 gas mixtures corresponding to the expected atmosphere of Venus was investigated experimentally in the electrically driven hypervelocity shock tube. These results are compared with heat transfer data in pure CO2 and pure N2. Calculations of radiative heat transfer contribution to the total heating are shown. Also, shock tube performance in two gas compositions as used in these experiments was computed. An attempt was made to measure radiant heat transfer to the stagnation region using the newly developed cavity gage.