Publication Date:
2019-06-27
Description:
Simulation experiments were performed in the NASA Langley Full Scale Tunnel to investigate the retroplume heating rates encountered by a lander vehicle during a terminal descent to a planetary surface. A 10% scale model of the Viking Lander with freestream velocity conditions from 37 to 75 ft/sec was used for simulation. The simulation test data were close to the theoretical predictions of Hill et al. (1971).
Keywords:
AERODYNAMICS
Type:
Journal of Spacecraft and Rockets; 10; Jan. 197
Format:
text
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