INVESTIGATION OF THE EFFECT OF TAPER STACKING LOCATION ON AERODYNAMIC LOADS FOR ONERA M6 WING AT A FIXED ANGLE OF ATTACK
The effect of taper stacking location for ONERA M6 wing is analyzed in terms of the lift, drag and lift-to-drag ratio. The stacking location is defined as the non-dimensional distance from the sectional leading edge to the taper axis. The non-dimensionalization is based on the sectional chord length. Different wing shapes are generated by linearly or parabolically varying the stacking location along the span. Various wing cases are investigated under the same angle of attack. The steady-state turbulent flowfields are computed by solving the Reynolds Averaged Navier-Stokes equations. The Spalart-Allmaras turbulence model with the extended wall function is used to calculate the eddy viscosity. It is observed that there exist some cases in which the values of lift, drag and lift-to-drag ratio change significantly. Moreover, the spanwise variation of the stacking location has a pronounced effect on the formation and the characteristics of the shock wave.
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