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).
Penetration of retrorocket exhausts into subsonic counterflows.
1973-01-01
Sonstige
Keine Angabe
Englisch
Parachute Retrorocket Airdrop System
NTIS | 1970
|Supercritical Combustion of General Fluids in Laminar Counterflows
British Library Conference Proceedings | 2013
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