Rapid prediction of high-alpha unsteady aerodynamics of slender-wingaircraft

Most aerospace vehicles, although designed for hypersonic cruise at low angles of attack, often have to perform rapid maneuvers at high angles of attack from low supersonic down to low subsonic speeds. There is, therefore, a need for rapid prediction of the nonlinear high-alpha vehicle dynamics of slender-wing aircraft in that speed range. The present paper describes such a prediction method, which can account for the nonlinear dynamic effects of leading-edge vortices at angles of attack, yaw, and roll. A comparison with existing experimental results shows that the accuracy of the prediction is satisfactory for preliminary design as long as breakdown of the leading-edge vortices does not occur.