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 to examine the effects of including flow nonlinearities in the prediction of this aeroelastic phenomenon. Transonic small disturbance theory is employed in the analysis of a simple rectangular wing and a typical fighter type wing to study the interactions among control surface deflections, structural flexibility, and embedded shocks in the flow field. Pressure distributions on the wings are examined. Rigid rolling moment calculations are presented, followed by control surface effectiveness and control surface reversal trends as the Mach number is varied from a subsonic value, through the transonic regime, into the supersonic region. These results are discussed based on the predictions of the pressure coefficients generated by the solution of the transonic small-disturbance equation. Finally, generalizations are presented about the effects of including aerodynamic nonlinearities in the prediction% of steady aeroelastic phenomenon in transonic flow conditions.