Investigation of Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-stream Mach Number of 1.39 (1956)
NASA Technical Reports Server (NTRS) · leaf 63
degrees JNACA M L55L13 Figure 21.- Variation of primary and secondary jet-on shock wave angles with nacelle-exit static-pressure ratio for a sonic exit.
NASA Technical Reports Server (NTRS)
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