NASA NTRS · 19730034689
Penetration of retrorocket exhausts into subsonic counterflows.
Abstract
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).
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Jarvinen, P. O., Hill, J. A. F.. 1973-01-01. Penetration of retrorocket exhausts into subsonic counterflows.. https://ntrs.nasa.gov/citations/19730034689
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