Further investigation of control surface reversal in the transonic regime

Abstract

This paper investigates control surface reversal in the transonic flight regime. Linear and nonlinear rigid and aeroelastic analyses are performed while including the effects of flow viscosity with an interactive boundary layer in the prediction of this aeroelastic phenomenon. Transonic small disturbance theory is employed in the analysis of a typical fighter type wing to study the interactions among control surface deflections, structural flexibility, and embedded shocks in a flow field where a viscous boundary layer exists. Pressure distributions on the wing are examined, and control surface reversal calculations are presented. These results are discussed based on the predictions of the pressure coefficients generated by the solution of the transonic small-disturbance equation. Generalizations are offered concerning the effects of including viscosity in the prediction of steady aeroelastic phenomena in the transonic flight regime. Finally, the consequences of these findings on the preliminary design of aircraft structures are discussed.