Performance of a supersonic ramp-type side inlet with ram-scoop throat bleed and varying fuselage boundary-layer removal : Mach number range 1.5 to 2.0 / Glenn A. Mitchell and Robert C. Campbell

Mitchell, Glenn A Campbell, Robert C
naca-rm-e56i26
January 17, 1957


Provided sufficient throat bleed was employed, maximum pressure recoveries of 0.87 to 0.88 at Mach number 2.0 were obtained for a fuselage-mounted 14 degrees ramp inlet regardless of the amount of fuselage boundary layer ingested. The addition of inlet side fairings yielded further increases in pressure recovery to 0.90 to 0.91, decreased critical drag coefficients, and increased critical mass-flow ratios. With throat bleed, peak pressure recoveries and calculated thrust-minus-drag values were comparable at two axial positions of the scoop and were highest with the greatest amount of fuselage boundary layer ingested.

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