Procedure determines supersonic-nozzle contours that allow higher nozzle-exit wall pressures, reducing chamber pressure without causing wall-flow separation as encountered in optimum large-area-ratio nozzle designs. Procedure applies to chemical-laser nozzles, jet-engine and gas turbines, wind tunnels and rocket nozzles.
Nonseparating High-Area-Ratio Supersonic Nozzles
NASA Tech Briefs ; 8 , 2
1984-11-01
Miscellaneous
No indication
English
Aspects of nonseparating apogee motors
AIAA | 1984
|NTRS | 1971
|AIAA | 1971
|AIAA | 1972
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