부산대학교 도서관

Numerical simulations of flowfields around an airfoil model mounted in the high-Reynolds-number, two-dimensional, transonic wind tunnel of the National Aerospace Laboratory are performed in this paper. Existence of four types of flow pattern at Mach numbers from 0.7 to 0.8, depending on an angle of attack and Reynolds number, is known from experimental studies for the BGK No. 1 airfoil. Present paper demonstrates to be able to simulate these flow patterns by numerical approach. The full Navier-Stokes equations with the Baldwin-Lomax turbulence model are solved by a cell-centered finite-volume method. The method utilizes the Roe's flux difference splitting scheme with third-order MUSCL approach for estimation of inviscid flux and the Galerkin-type approximation which results in central-difference-like formulas for viscous flux. Simulated flowfields are compared with experimental data in very good agreement. The flowfields are analyzed in detail.