APPROXIMATE VISCOUS SHOCK-LAYER METHOD FOR HYPERSONIC FLOW OVER BLUNT-NOSED BODIES

An approximate axisymmetric method is presented that can calculate the surface and flowfield properties accurately for the fully viscous hypersonic flow over blunt-nosed bodies. Using the second-order pressure equation of Maslen and incorporating viscous terms into the streamwise momentum and energy equations, a simple method is obtained which can calculate both the subsonic and supersonic regions of the shock layer and does not require a starting solution for the shock shape. The turbulence model of Cebeci-Smith and the equilibrium air tables of Hansen are incorporated into the method. The method is faster than the parabolized Navier-Stokes or viscous shock-layer solvers it might replace in a preliminary design environment. Hyperboloid and sphere cone configurations at 0-deg angle of attack and with half-angles up to 45 deg have been successfully run to convergence. Surface heat-transfer and pressure predictions from the present method compare very well with the more accurate viscous shock-layer method, flight and wind-tunnel data. Distributions of flowfield properties across the shock layer also compare very well between the two methods. Because the present viscous method does not require a starting solution, it could be used to provide more accurate shock shapes for higher-order methods which currently use inviscid starting solutions.