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Supersonic inlet contour interpolationA method for designing supersonic inlet contours is described which consists in the interpolation of the contours of two known inlets designed for different Mach numbers, thereby determining the contours for a third inlet at an intermediate design Mach number. Several similar axisymmetric inlet contours were interpolated from known inlets with design Mach numbers ranging from 2.16 to 4.0 and with design Mach numbers differing by as much as 1.0. The flowfields were calculated according to Sorensen's (1965) computer program. Shockwave structure and pressure distribution characteristics are shown for the interpolated inlets. The validity of the interpolation is demonstrated by comparing the plots of the flowfield properties across the throat station of the interpolated inlet with the known inlets which were designed iteratively. It seems possible to write a computer program so that a matrix of known inlet contours can be interpolated.
Document ID
19760032001
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Sorensen, N. E.
(NASA Ames Research Center Moffett Field, CA, United States)
Latham, E. A.
(NASA Ames Research Center Aerodynamics Branch, Moffett Field, Calif., United States)
Date Acquired
August 8, 2013
Publication Date
September 1, 1975
Publication Information
Publication: Journal of Aircraft
Volume: 12
Subject Category
Aerodynamics
Accession Number
76A14967
Distribution Limits
Public
Copyright
Other

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