Simulation of Aircraft Response to Control Surface Deflection Using Unstructured Dynamic Grids

Abstract

The computational techniques required for flight-test simulation in which the deflection angle of a tail wing is changed are discussed. To treat the computational grid for a moving control surface, an unstructured dynamic mesh method with surface-grid movement is used. This method is applied to the numerical simulation of the control-surface response for an experimental supersonic airplane at the National Aerospace Laboratory of Japan. Its high capability is demonstrated in both steady and unsteady simulations.