Numerical and experimental determination of secondary separation on delta wings in subsonic flow

The flow over a delta wing at incidence separates at the leading edge and reattaches on the upper surface. As the flow moves spanwise from the reattachment line, a secondary separation line forms near the leading edge and both lines lie on conical rays through the vertex of the wing. A quasi-three-dimensional laminar boundary-layer method is developed for conical inviscid flows that uses a predictor-corrector finite difference computational technique. A similarity solution is calculated at the reattachment line; then the solution is marched spanwise toward the leading edge until secondary separation is encountered. Also, the solution is marched inward from the reattachment line to the root chord.