Scope and method of study. The purpose of this study was to examine the effects that asymmetric flap deflection has on delta wings. The study was performed using computational and experimental methods. Computational studies were performed using an inviscid computer model that was coupled with the rigid body equation of motion in oscillations to simulate the fluid structure interaction. Investigation focuses on an isolation of quasi-steady effects on a delta wing through an application of the roll-rate boundary conditions. Spanwise camber changes through differential flap deflection was investigated. Experimental measurements on roll moment and pressure distribution over a 65;Findings and conclusions. Computational results indicate that quasi-steady effects have a damping effect on the motion primarily because of the hysteresis behavior of vortex position normal to the wing. Spanwise camber when applied proportional to roll rate has been shown to be capable controlling the wing when in roll. Experimental results indicated that asymmetric flap deflection (left flap downward, right flap upward) present 3 different behavior on the wings as the angle of attack changes. The 80
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