This report presents a novel method of generating13; comprehensive aerodynamic data of aircraft using Dynamic13; wind tunnel simulation. The method combines measurement13; of motion and force responses of aircraft model to control13; inputs. The aerodynamic data generated includes trimmed13; Lift characteristics, Longitudinal stability derivatives, Neutral point, and large amplitude Lift and pitching moment responses to arbitrary control surface inputs.13; The advantage of the method is the simple instrumentation and wind tunnel tests.13; The method is demonstrated using a generic delta winged aircraft model with pitch DOF flown in a low speed dynamic wind tunnel. The model pitch attitude and Lift responses to elevon inputs are measured and used to deduce longitudinal aerodynamic data. Comparison of these13; results with Datcom estimates and static test data of a similar configuration show good agreement, thus validating the method
