Abstract
The high speed flow over a sharp-edged plane delta wing with 65° sweep has been investigated experimentally as well as computationally. The experimental program contains surface pressure measurements, oil flow and Schlieren visualization at Mach numbers from 0.7 to 0.9 and angles of attack up to 20°. Attention was paid to the presence of embedded shocks, vortex breakdown and the interaction between them. Special emphasis is given to the case with a free stream Mach number of 0.85. At this Mach number and angles of attack of 15° and higher, a shock is observed across the wing symmetry plane. Beyond 18° angle of attack the breakdown of both leading edge vortices is observed going along with a double shock system across the symmetry plane: one at about 50% chord position and one at 80%. Downstream of the first shock a strong expansion is present.
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