A Parametric Study of Circulation Control Airfoils
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Investigation of characteristics of circulation control airfoils on a delta wing configuration, with a view to optimising lift within the limits of pitch trim. Different trailing edge geometries (eg. variation of trailing edge diameter and gap height) have been investigated and the effect of the leading edge vortex from a 50° swept delta wing (previous work showed little effect of sweep angle) on the characteristics of circulation control were studied. Aim to apply to military aircraft, possibly replacing current conventional control surfaces (eg flaps). Future work will investigate a full span model, incorporating 2 circulation control units, such that roll control may also be achieved.