Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8
1956-07-01
Miscellaneous
No indication
English
Investigation of two-step nozzle in Langley 11-inch hypersonic tunnel
Engineering Index Backfile | 1950
|The Langley 15-inch Mach 6 High Temperature Tunnel
AIAA | 1992
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