Flight determination of drag and pressure recovery of a nose inlet of parabolic profile at Mach numbers from 0.8 to 1.7

Richard I. Sears, C. F. Merlet
naca-rm-l51e02
Oct 1951


A ducted model having a nose inlet whose external contour was defined by a parabolic arc was flight-tested at zero angle of attack. External drag coefficient and total-pressure recovery at the end of the diffuser were measured over a range of Mach numbers from 0.8 to 1.7 and a range of mass-flow ratios from 0.23 to 1.0.

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