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Comparisons of numerical and exact solutions for oblique detonationswith structure

Numerical predictions of the two-dimensional, inviscid, supersonic, reactive flow of a calorically perfect ideal gas over a straight wedge are compared with the predictions of a linear asymptotic model valid in the hypersonic limit. Solution features predicted by the asymptotic model include a curved shock attached to the wedge tip, a reaction layer parallel to the shock, and a vorticity layer parallel to the wedge surface. For sufficiently high Mach number and heat release, the numerical model predicts similar behavior, and the differences in the predictions of the two methods are of the same order of magnitude as the inherent error of the asymptotic method. As heat release is lowered and Mach number held constant, apparent numerical artifacts obscure features predicted by the asymptotic method. The results suggest that the asymptotic solution has utility as a benchmark to verify the predictions of many high-speed, multidimensional, reacting flow codes.