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| Title: |
Thin airfoil theory based on approximate solution of the transonic flow equation
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| Author(s): |
Spreiter, John R; Alksne, Alberta Y
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| Abstract: |
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.
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| NASA Center: |
Ames Research Center
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| Publication Year: |
1958 |
| Document Source: |
CASI |
| Online Source: |
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| Document ID: |
19930091016
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| Accession ID: |
93R20306
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| Publication Information: |
Number of Pages = 37 |
| Report Number: |
NACA-TR-1359
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| Price Code: |
A03 |
| Related Information: |
Also bound with NACA Annual Report 44-VOL-1, p. 509-545.Supersedes NACA Technical Note 3970.; NACA Technical Report 1359. |
| Keywords: |
THIN WINGS; NONLINEAR EQUATIONS; EQUATIONS OF MOTION; APPROXIMATION; TRANSONIC FLOW; FLOW THEORY; COMPUTATIONAL FLUID DYNAMICS; TWO DIMENSIONAL FLOW; FREE FLOW; MULTIPHASE FLOW; WING PROFILES; PRESSURE DISTRIBUTION; SUPERSONIC FLOW; SUBSONIC FLOW; MACH NUMBER; PRESSURE DRAG; INTEGRAL EQUATIONS; MACH NUMBER;
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| Accessibility: |
Unclassified; No Copyright; Unlimited; Publicly available; |
| Updated/Added to NTRS: |
2009-01-14 |
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