Abstract:

Algebraic method combined with optimal elliptic partial differential equations is used to generate multiblock grids for a wing/body junction. Finitevolume scheme and five-stage Runge-Kutta explicit scheme are applied to solve the three-dimensional N-S equations. Based on Reynolds-Averaged N-S（RANS）equations, Spalart-Allmaras（SA） OneEquation turbulence model is employed to simulate the turbulent flows. A steady N-S solver is applied to the wing/body junction in transonic flight, then the buffet onset angle of shock induced buffet is reasonably estimated with various steady aerodynamic parameters of lift curve, pitching moment curve, tailing edge pressure deviation, reversal in shock movement and wing surface streamlines.

Key words: multiblock , grids,  , finitevolume , method,  , N-S , equations,  , turbulence , model,  , buffet