Control surface reversal in the transonic regime

Abstract

A method of predicting control-surface reversal trends in the transonic flight regime is presented. 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 flowfield. 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. Results indicate the importance of including aerodynamic nonlinearities in the steady aeroelastic analysis and design of lifting surfaces with deflected control surfaces subject to transonic flow conditions.