The aerodynamic characteristics of the Apollo Command Module in the hypersonic low density regime were investigated. The experiments were performed in the hypersonic low density tunnels at the AVA Research Center of the DFVLR. This wind tunnel investigation includes: (1) drag measurements at zero lift, (2) three component force measurements, and (3) heat transfer measurements. The results are compared with pertinent U.S. experiments. (Author)
APOLLO Command Module Aerodynamic Simulation Test in Hypersonic Flow
1971
25 pages
Report
No indication
English