Internal performance of several auxiliary air inlets immersed in a turbulent boundary layer at Mach numbers of 1.3, 1.5, and 2.0

Huff, Ronald G Anderson, Arthur R
naca-rm-e56j18
January 18, 1957


Internal performance of normal-shock rectangular, circular, and scoop inlets and of external-compression inlets experimentally obtained with varying immersion in a turbulent boundary layer. Recoveries varied from about 95 percent of theoretical in the free stream to 80 percent with complete immersion, while the corresponding mass flows were usually above 95 percent of theoretical. Turning of the flow through 10 degrees caused losses in pressure recovery of 0.03 to 0.07. External compression did not improve pressure recovery in the boundary layer. Average distortion at critical operation for all inlets was 5 percent.

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