Evaluation of NCOREL, PAN AIR, and W12SC3 for Supersonic Wing Pressures

The ability of three recently developed computer programs to predict pressures on a supersonic maneuver wing has been evaluated. The NCOREL program was the only code capable of predicting the nonlinear leeward leading edge supercritical crossflow and resultant shock wave formation at the higher angles of attack Both linear panel methods, PAN AIR and W12SC3, performed reasonably well at the lower angles of attack Im plementing the freestream axis as the compressibility axis, PAN AIR overpredicted the windward pressures in comparison to the W12SC3 program at higher angles of attack