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Thin airfoil theory based on approximate solution of the transonic flow equationA method is presented for the approximate solution of the nonlinear equations of transonic flow theory. Solutions are found for two-dimensional flows at a Mach number of 1 and for purely subsonic and purely supersonic flows. Results are obtained in closed analytic form for a large and significant class of nonlifting airfoils. At a Mach number of 1 general expressions are given for the pressure distribution on an airfoil of specified geometry and for the shape of an airfoil having a prescribed pressure distribution. Extensive comparisons are made with available data, particularly for a Mach number of 1, and with existing solutions.
Document ID
19930091016
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Spreiter, John R
Alksne, Alberta Y
Date Acquired
September 6, 2013
Publication Date
January 1, 1958
Report/Patent Number
NACA-TR-1359
Report Number: NACA-TR-1359
Accession Number
93R20306
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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