Slender-body theory based on approximate solution of the transonic flow equation /
by John R. Spreiter and Alberta Y. Alksne.

Description

Main Author

Spreiter, John R.

Related Names

Alksne, Alberta Y.
United States. National Aeronautics and Space Administration.
Ames Research Center.

Language(s)

English

Published

Washington, DC : U.S. G.P.O., 1959.

Subjects

Aerodynamics > Aerodynamics / Research > Aerodynamics / Research / United States.
Body of revolution > Body of revolution / Research > Body of revolution / Research / United States.

Summary

Approximate solutions of the nonlinear equations of the small disturbance theory of transonic flow are found for the pressure distribution on pointed slender bodies of revolution for flows with free-stream Mach number 1, and for flows that are either purely subsonic or purely supersonic. These results are obtained by application of a method based on local linearization that was introduced recently in the analysis of similar problems in low-dimensional flows. The theory is developed for bodies of arbitrary shapes, and specific results are given for cone-cylinders and for parabolic-arc bodies at zero angle of attack. All results are compared either with existing theoretical results or with experimental data.

Note

"Report date Nov. 26, 1958."

Physical Description

54 p. : ill. ; 26 cm.

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