The Compressible Inviscid Vortex Flow of a Sharp Delta Wing

Kurzfassung

An analysis is presented on the compressible inviscid vortex flow over three delta wings with sharp leading edges with leading edge sweep angles 60, 70 and 76 degrees using numerical solutions of the Euler equations. Presentations of results are given for Mach numbers ranging from M &#61 0.1 to 0.8 and for angles of attack up to the onset of vortex breakdown. The paper focusses the attention on the effects of the vortex flow on the flow field of a delta wing. The occurence of shock waves of two types: cross-flow and terminating (or rear) shocks induced vortex breakdown and the effects of compressibility on the rapid performance degradation of delta wings after vortex bursting are studied in detail. Moreover, the changes on flow kinematic within the vortex core due to the close presence of the wing are also studied.