The flowfield in the plane of symmetry of a thin lifting delta wing with supersonic leading edges is examined for wings with apex angles that are comparable to the Mach angle, as well as for the limiting case of a straight leading edge. For these two cases, a simplified treatment of the interaction between the plane expansion wave emanating from the trailing edge and the three-dimensional bow shock is presented. In the region unaffected by the wing tips, the shock decays inversely with distance from the wing.
Flowfield in the plane of symmetry below a delta wing
AIAA Journal ; 14
1976-02-01
Sonstige
Keine Angabe
Englisch
Flowfield in the plane of symmetry below a delta wing
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