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Effect of Subsonic Inlet Lip Geometry on Predicted Surface and Flow Mach Number DistributionsThe effect of subsonic inlet lip geometry on predicted surface and flow Mach number distributions is illustrated. The theoretical results were obtained from incompressible potential flow calculations corrected for compressibility. The major emphasis of this investigation is on the low-speed (takeoff and landing) operating conditions. The low-speed results were obtained for a range of three geometric variables of interest: contraction ratio, defined as the ratio of highlight area to throat area; internal lip major - to minor-axis ratio; and internal lip shape. The low-speed results were obtained at both static conditions and a free-stream velocity of 42.6m/sec, with incidence angles ranging from 0 deg to 50 deg. The results indicate that of the three geometric variables considered, contraction ratio had the largest effect on the surface Mach number distributions. The effects of inlet diameter ratio and blunting of the external forebody on maximum external surface Mach numbers are illustrated at a cruise Mach number of 0.8.
Document ID
19740003699
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Albers, J. A. (NASA Lewis Research Center Cleveland, OH, United States)
Miller, B. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1973
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-7446
E-7522
Accession Number
74N11812
Funding Number(s)
PROJECT: RTOP 501-24
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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