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
38 S
Ill., graph. Darst
Digital preservation by Technische Informationsbibliothek (TIB) / Leibniz-Informationszentrum Technik und Naturwissenschaften und Universitätsbibliothek
Book
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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