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 65
o\ 4=- … Figure 23.- Variation of the point of intersection on the center line of the wing of the secondary shock wave with nacelle-exit total-pressure ratio at test positions Ia, lb* anc^ Iq as measiire(i from the shadow- graph pictures.
NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
