Transonic porous wall interference characteristics of the low aspect ratio flying wing model in FL-2 wind tunnel

In order to meet the elaborateness requirements of modern wind tunnel testing and improve the accuracy of wind tunnel test data, the nonlinear method of transonic porous wall interference corrections based on wall pressure is developed. The measured wall pressure information is adopted to construct the porous wall boundary conditions, and the flow field around the test model in the wind tunnel is simulated numerically with the N-S equations. Unlike the linear correction methods, this method can be used for a variety of complex shapes of the aircrafts to correct the porous wall interference in the subsonic or transonic wind tunnel. The characteristics of wall interference corrections is studied combining with test data of the low aspect ratio flying wing model conducted in the FL-2 wind tunnel. The results indicate that the wall interference has a rising trend with the Mach number increasing, the interference reaches to the maximum at about Ma=1.0, and the corrected results of the FL-2 wind tunnel test data are in good agreement with the test results of the FL-26 wind tunnel approximately without interference.