Numerical and experimental modeling of supersonic flow regimes around a delta wing
M.D. Brodetsky1, A.V. Zabrodin2, A.E. Lutsky2, A.M. Kharitonov1, A.M. Shevchenko1
1Institute of Theoretical and Applied Mechanics SB RAS, Novosibirsk, Russia
2Keldysh Institute of Applied Mathematics RAS, Moscow, Russia
Pages: 163-183
Abstract
Results of numerical and experimental investigations of supersonic flow regimes around a delta wing with a sweep angle of 78o for a Mach number of 2.75 and angles of attack of 6, 8, 18, and 20o are described. The computations are performed within the framework of three-dimensional Euler equations with a zonal approach. A comparative analysis of results of numerical and physical experiments and verification of the numerical model developed are performed. It is shown that the computation method allows adequate simulation of the basic specific gas-dynamic features of the flow past the leeward side of the delta wing.
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