Abstract:

A numerical method is used to compute the hypersonlc, nonequilibrium, viscous shock-layer flow over a blunt wedge. A truncated series is used to develop the differential equations at the stagnation streamline. As a result, the initial value for the viscous shock-layer equations can be improved. The continuity equation and the transversal momentum equation are solved in a coupled way, so that the calculations can be matched with the solutions at far downstream of the planar blunt-bodies. The numerical results are given and compared with those from other methods.

Key words: numerical calculation, hypersonic flow, viscous flow, chemical reacting flow, planar flow, blunt body