Results obtained from iterative solutions of inviscid and boundary-layer equations are presented and compared with experimental values. The calculated results were obtained with an Euler code and a transonic potential code in order to furnish solutions for the inviscid flow; they were interacted with solutions of two-dimensional boundary-layer equations having a strip-theory approximation. Euler code results are found to be in better agreement with the experimental data than with the full potential code, especially in the presence of shock waves, (with the sole exception of the near-tip region).
Interactive boundary-layer calculations of a transonic wing flow
Journal of Aircraft ; 26
1989-04-01
Miscellaneous
No indication
English
Calculations Of Transonic Flow About A Wing
NTRS | 1988
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British Library Conference Proceedings | 2006
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