Preliminary investigation of effects of combustion in ram jet on performance of supersonic diffusers I : shock diffuser with triple-shock projecting cone

J. F. Connors, A. H. Schroeder
naca-rm-e8f15
Sep 1948


A preliminary investigation was conducted in the NACA Cleveland 20-inch supersonic tunnel at a Mach number of 1.92 with a 3.6-inch-diameter ram jet to determine the effects of combustion on the performance of a shock diffuser with a triple-shock projecting cone. Results are presented for a range of outlet areas and fuel flows with both single- and split-fuel-injection systems.

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