Numerical solution of the problem of supersonic flow past wings of arbitrary form with a detached shock wave
A numerical method has been developed to calculate supersonic inviscous gas flow around wings of arbitrary form with a shock wave detached from the leading edge. The solution domain is divided into three subdomains. A total algorithm is formed from the specific ones of each subdomains, depending on the wing configuration. For the front part of the wing where the flow is subsonic and supersonic the problem is solved by using the time-dependent stationary principle. The remaining parts of the wing including its tip side are treatea as three-dimensional stationary cases. A number of test cases are computed for the flow around the wings of various configurations.
KeywordsShock Wave Supersonic Flow Front Part Solution Domain Delta Wing
Unable to display preview. Download preview PDF.
- 2.G.P. Voskresensky, M.G. Orlova, and V.A. Stebunov. A supersonic inviscous flow around wings with a detached shock wave. Preprint IPM AN SSSR, N 152, 2981.Google Scholar