CALCULATION OF WALL AND MODEL SUPPORT INTERFERENCES IN SUBSONIC WIND-TUNNEL FLOWS

For the correlation of results from cryogenic wind tunnel experiments at high Reynolds numbers with corresponding full scale flight test data, detailed wind tunnel boundary and model support interferences are calculated. The simulated wind tunnel consists of the cryogenic subsonic wind tunnel KKK at DLR Koln and the test model is the transonic wing demonstrator aircraft TST Alpha-Jet. For the calculations a reliable and well tested 3D-panel method is used. The results are given in the form of coefficient corrections for the main aerodynamic model coefficients lift, drag and pitching moment.