On the Effect of Area Ruling on Transonic Abrupt Wing Stall

Reynolds-averaged Navier-Stokes simulations of the transonic flow over a generic fighter aircraft wing/LEX/body configuration are presented. Data in the pre and post-stall regime are presented, and it is shown that small changes in the cross-sectional area distribution in the aft body has a significant effect on the onset of wing stall, but more systematic computations are needed before the effectiveness of area-ruling can be firmly established.