Application of NLR's calculation methods to transonic flow about oscillating wings

Abstract

Unsteady and quasisteady aerodynamic loads in the transonic flow domain have been obtained from the numerical simulation methods of the National Aerospace Laboratory (NLR) for transonic potential flow. The unsteady results have been obtained with the time-linearized finite volume method FTRAN3, embedding a socalled field panel method which accounts for proper radiation of signals toward infinity. The mean steady flowfields and the quasisteady results have been obtained from the application of XFLO22-the NLR system for the simulation of steady transonic flow about wings and wing bodies. The calculations have been performed for several wing planforms and the results are compared with experimental data. A correlation is made between the quasisteady results of XFLO22 and FTRAN3. Flutter applications to a transonic transport wing model and a fighter configuration have been made.