Flow around wings accompanied by separation of vortices /
The flow around wings computed by the usual method leads in the case of a finite trailing edge to a stagnation point in the trailing edge due to the Kutta-Joukowsky condition of flow governing this region. As a result, the theoretical pressure distribution differs substantially from the experimental...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington, D.C. :
National Advisory Committee for Aeronautics,
[1940]
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| Series: | Technical memorandum (United States. National Advisory Committee for Aeronautics) ;
no. 961 |
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Internet
This item is not available through BorrowDirect. Please contact your institution’s interlibrary loan office for further assistance.Stanford University
| Call Number: |
ISIL:US-CST NACA TM 961 |
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