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 64
Figure 22.- Variation of the angle between the point of intersection on the wing of the primary shock wave and the nacelle exit with nacelle- ON exit static-pressure ratio for the three vertical positions tested. v>j
NASA Technical Reports Server (NTRS)
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