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Theoretical Performance Characteristics of Sharp Lip Inlets at Subsonic SpeedsA method is presented for the estimation of the subsonic-flight-speed characteristics of sharp-lip inlets applicable to supersonic aircraft. The analysis, based on a simple momentum balance consideration, permits the computation of inlet pressure recovery - mass-flow relations and additive-drag coefficients for forward velocities from zero to the speed of sound. The penalties for operation of a sharp-lip inlet at velocity ratios other than 1.0 may be severe; at lower velocity ratios an additive drag is incurred that is not cancelled by lip suction, while at higher velocity ratios, unavoidable losses in inlet total pressure will result. In particular, at the take-off condition, the total pressure and the mass flow for a choked inlet are only 79 percent of the values ideally attainable with a rounded lip. Experimental data obtained at zero speed with a sharp-lip supersonic inlet model were in substantial agreement with the theoretical results.
Document ID
19930083660
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Technical Note
Authors
Fradenburgh, Evan A (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Wyatt, Demarquis D (National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. Cleveland, OH, United States)
Date Acquired
August 16, 2013
Publication Date
September 1, 1953
Subject Category
Aerodynamics
Report/Patent Number
NACA-TN-3004
Accession Number
93R12950
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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