Abstract
For a fighter type aircraft like the TST Alpha-Jet model the aerodynamic coefficient corrections for unsymmetric windtunnel flows are calculated. The model is attached to a rear sting support system and placed in the test-section of a subsonic windtunnel (KKK at DLR Köln) at incidence and yaw. For the numerical simulation of the windtunnel flow a subsonic panel method is used. The results are given in the form of windtunnel and support corrections for the lateral model coefficients side force, yawing and rolling moment.
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