Four models of Mars entry vehicles tested were a sphere with cg=35 percent (measured in percent of diameter from surface); Apollo with cg=16 percent (measured in percent of maximum diameter rearward of heat shield); a 103-degree cone with cg=20 percent (measured in percent of maximum diameter rearward of small end); and a tension structure: cg=25 percent (measured in percent of maximum diameter rearward of small end).
Model Test of Mars Entry Vehicles in Langley Spin Tunnel
1964-10-08
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English
Earth entry flight test of mars entry vehicles
AIAA | 1965
|Earth entry flight test of Mars entry vehicles.
AIAA | 1966
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