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Performance of variable two-dimensional inlet designed for engine-inlet matching I : performance at design Mach number of 3.07The inlet was investigated with both a two-oblique-shock and an isentropic compression ramp. Provisions for a variety of bypass systems were incorporated and none decreased pressure recovery by more than about 1 percent. By utilizing throat boundary-layer control, critical pressure recoveries of 64 and 70 percent were obtained with the two-shock and isentropic ramps, respectively. Diffuser-exit air distortion was about 5 percent at critical operation Theoretical cowl pressure drag was equal to about 10 percent of the net thrust of an assumed engine.
Document ID
19930089586
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Beheim, M A
Gertsma, L W
Date Acquired
August 29, 2013
Publication Date
October 20, 1956
Report/Patent Number
NACA-RM-E56H23
Accession Number
93R18876
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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