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Thin airfoil theory based on approximate solution of the transonic flow equation
- Author / Creator
- Available as
- Online
- Summary
-
A 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 a...
A 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.
Details
- Creator
- by John R. Spreiter and Alberta Y. Alksne
- Format
- Books
- Language
- English
- Contributors
- Publication
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- Washington, D.C. : National Advisory Committee for Aeronautics, 1957
- Physical Details
-
- 1 online resource (82 pages) : illustrations ; 27 cm
- data file
- OCLC
- on1401646879
- Report numbers NACA-TN-3970.
- Date of issue: May 1957.
- "Ames Aeronautical Laboratory."
- Title from title screen (viewed September 14, 2023)
- Includes bibliographical references (pages 79-82)
- Electronic reproduction. Denton, Texas : University of North Texas, 2011. Electronic reproduction from print master produced by University of North Texas.