Application of eN method in three-dimensional hypersonic boundary layers

A simple algorithm of saddle-point method (SPM) in eN method was presented by using internal wave theory, and distribution of N was computed on a model made up of plate, cone and cylinder at the cases of 30-45 km altitudes, Mach number of 10, attack angles of 0° and 10°. The results and conclusions show that: as the altitude increases, the transition position moves downstream, and the transition area becomes smaller and even disappears. On the plate part (windward side), the transition possibility in 10° attack angle cases is bigger than that in 0° attack angle cases, and the transition area is larger too. But on the cone part (leeward side), the transition possibility in 10° attack angle cases is less, and the transition area is smaller, even inexistence. And the transition positions of these two series of cases are different.