Validation of Unsteady Aerodynamic Models of a Generic UCAV Configuration

This work is part of the NATO STO Task Group AVT-201 Special Sessions being organized by the AIAA Applied Aerodynamics Technical Committee. Teduced-Order Modeling techniques based on response functions are presented and validated for unsteady aerodynamic prediction of a generic UCAV with trailing edge flaps. A hybrid unstructured mesh was generated to move these control surfaces and simulate the flow fields around the vehicle with a sting geometry available in the experiments. The Reynolds-averaged Navier Stokes flow topology over the configuration is described for a range of angles of attack and control surface deflections. Validation results also highlight the effects of gaps present in the overset mesh on the predictions. The response functions with respect to angle of attack, pitch rate, and flap deflections are directly calculated from step motion simulations in CFD and a grid motion approach.