Aeroelastic analysis of rolling maneuvers with multiple control surfaces in transonic flight

Abstract

This study investigates the use of multiple control surfaces to generate rolling maneuvers in the transonic flight regime. Linear and nonlinear aeroelastic analyses are performed to examine the effects of including flow nonlinearities in the prediction of roll performance generated through the utilization of leading and trailing edge control surfaces. Transonic small disturbance theory is employed in the analysis of a simple rectangular wing to study the interactions among control surface deflections, structural flexibility, and embedded shocks in the flow field. Pressure distributions on the wing are examined. Rolling moment calculations are presented as the Mach number is varied from a subsonic value through the transonic regime. These results are discussed based on the predictions of the pressure coefficients generated by the solution of the transonic small disturbance equation. Generalizations are then presented about the effects of including aerodynamic nonlinearities in the prediction of steady state roll rates caused by multiple control surface deflections in transonic flow conditions.