Estimation of aerodynamic derivatives using Dynamic Wind Tunnel Simulation Technique

This paper presents the results of estimation of the longitudinal and lateral aerodynamic derivatives of a delta winged aircraft model using Dynamic Wind Tunnel Simulation Technique. Experiments are conducted using single rotary degree freedom in pitch, roll, and yaw axes. Test inputs are applied to the appropriate servo controlled control surfaces namely symmetric elevon, differential elevon, and rudder to excite the model in pitch, roll, and yaw respectively. The characteristic motion response of the model to the applied test inputs is analyzed using parameter estimation techniques to extract the aerodynamic derivative data. The results are compared with derivatives obtained from conventional testing methods namely static wind tunnel test, free oscillation rig, and forced oscillation rig which use force/moment data obtained from the model strain gauge balance. A recently developed method of computing neutral point using parameter estimation technique is used to determine the same for this model. (Author