Approximate method for calculation of laminar boundary layer with heat transfer on a cone at large angle of attack in supersonic flow / William E. Brunk.
By the use of an integral technique, the laminar boundary-layer equations are reduced on the windward generator of the plane of symmetry to a set of simultaneous algebraic equations. The Chapman-Rubesin temperature-viscosity relation and a Prandtl number of 1 are assumed. The method enables the skin...
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| Format: | Government Document Book |
| Language: | English |
| Published: |
Washington :
National Advisory Committee for Aeronautics,
[1958]
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| Series: | Technical note (United States. National Advisory Committee for Aeronautics) ;
4380. |
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PASCAL Offsite
| Call Number: |
Y 3.N 21/5:6/4380
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| Y 3.N 21/5:6/4380 | Available Place a Hold |