Convective and radiative heating for vehicle return from the Moon and Mars

The aerothermal environment is examined for two vehicle forebodies near the peak heating points of lunar and martian return-to-earth trajectories at several nominal entry velocities. The first vehicle forebody is that of a 70 deg aerobrake for entry into earth orbit; the second, a capsule of Apollo...

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Bibliographische Detailangaben

Hauptverfasser:	Greendyke, Robert B., Gnoffo, Peter A.
Format:	Report
Sprache:	eng
Schlagworte:	Fluid Mechanics And Heat Transfer
Online-Zugang:	Volltext bestellen
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