Abstract
Conclusions Parametric calculations of supersonic flowfields around a series of rhombic delta wings were carried out to construct a correlation law for predicting the shock angle in the plane of symmetry of the wing. The computed shock angles were correlated by a parameter comprising Mach number, the theoretical two-dimensional oblique shock angle, and the angle between the plane of symmetry and the face of the rhombic wing. By approximating the correlated data using a polynomial fit, a correlation law of the shock angle with supersonic Mach number and wing geometry has been constructed.
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