Steady, 2D Euler flow computations have been performed for a wind tunnel section, designed for research on transonic shock wave - boundary layer interaction. For the discretization of the steady Euler equations, an upwind finite volume technique has been applied. The solution method used is collective, symmetric point Gauss-Seidel relaxation, accelerated by nonlinear multigrid. Initial finest grid solutions have been obtained by nested iteration. Automatic grid adaptation has been applied for obtaining sharp shocks. An indication is given of the mathematical quality of four different boundary conditions for the outlet flow. Two transonic flow solutions with shock are presented; a choked and a non-choked flow. Both flow solutions show a good shock capturing. A comparison is made with results obtained by holographic interferometry. Keywords: steady Euler equations - transonic flows - mutigrid methods - grid generation and adaptation - boundary conditions
|Titel||Papers Presented at the V. Aerodynamic Seminar of Lehrgebiet Aerodynamik Des Fluges, Technical University Aachen (RWTH) on July (5 - 7), 1987|
|Plaats van productie||Hanau|
|Uitgeverij||Haag + Herchen|
|ISBN van geprinte versie||9783925714320|
|Status||Gepubliceerd - 1990|
|Naam||Proceedings of High Speed Aerodynamics|
Koren, B. (1990). Euler flow solutions for transonic wind tunnel section. In A. Nastase (editor), Papers Presented at the V. Aerodynamic Seminar of Lehrgebiet Aerodynamik Des Fluges, Technical University Aachen (RWTH) on July (5 - 7), 1987 (blz. 14-26). (Proceedings of High Speed Aerodynamics; Vol. II). Haag + Herchen.