CALCULATION OF THE LATERAL COEFFICIENT CORRECTIONS FOR AN AIRCRAFT MODEL WITH REAR STING SUPPORT IN SUBSONIC WINDTUNNEL FLOW

For a fighter type aircraft like the TST Alpha-Jet model the aerodynam ic coefficient corrections for unsymmetric windtunnel flows are calcul ated. The model is attached to a rear sting support system and placed in the test-section of a subsonic windtunnel (KKK at DLR Koln) at inci dence and yaw. For the numerical simulation of the windtunnel flow a s ubsonic panel method is used. The results are given in the form of win dtunnel and support corrections for the lateral model coefficients sid e force, yawing and rolling moment.