FAST TRANSONIC CORRECTIONS FOR PANEL METHODS USING VISCOUS-INVISCID INTERACTION

This work presents a methodology for quickly computing unsteady aerodynamic loads and flutter in the transonic regime within the context of preliminary aircraft design. The approach relies on correcting an unsteady three-dimensional source and doublet panel method using a recently developed transonic correction technique. The reference steady three-dimensional solutions needed to apply the correction are computed by means of a novel
viscous-inviscid interaction scheme, whereby a steady full potential solver is coupled to the unsteady integral boundary layer equations through a quasi-simultaneous scheme. The methodology is applied to the LANN and the AGARD wing test cases. Overall, the present approach is found to improve the prediction of the aerodynamic pressure loads and of the transonic flutter dip. The main next step consists in integrating the methodology into an optimization framework in order to calculate flutter constraint quickly.