Numerical calculation of transonic flow past a swept wing by a finite volume method
- 1 January 1977
- report
- Published by Office of Scientific and Technical Information (OSTI)
Abstract
The finite volume method for the numerical calculation of transonic flow past a swept wing was developed and its use for calculating the pressure distribution on the upper surface of a Onera m6 wing in Mach No. 0.84 flow and of a Douglas DC10 wing in M = 0.85 flow is illustrated. Calculated results are compared with experimental data. The results confirm the promise of the new method. It appears that it can be used to treat configurations of more or less arbitrary complexity, subject to limits set by the power of the available computers. The extension to new configurations is primarily a matter of devising mesh generating schemes, since the internal computations are essentially independent of the configuration, apart from the identification of which elements are the boundary elements. (LCL)Keywords
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