Thrust, boundary layer, and heat transfer characteristics were computed for exhaust nozzles for propulsion device, having radial flow in divergent part; results were generalized independent of divergence angle and of stagnation pressure in temperature range of 1000 to 3000 C; means of determining aerodynamically optimum wall is provided.
Estimated performance of radial-flow exit nozzles for air in chemical equilibrium
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 1-5-59E
1959
53 pages
Aufsatz (Zeitschrift)
Englisch
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