Numerical Computation of Hypersonic Viscous Flow over a Sharp Leading Edge

C = Chapman-Rubesin constant, /iw Tao/fj,aoTw e = specific internal energy E = total energy, e + (u + v)/2 k = coefficient of thermal conductivity M = Mach number p = pressure Pr = Prandtl number Rex = Reynolds number T = temperature Tg = gas temperature at the wall u, v = velocity components in x, y directions v = rarefaction parameter, MQO(C/JR^je)°' x, y = distances along and normal to plate y = specific heat ratio by = Kronecker delta A = mean free path of the gas \L = viscosity coefficient p = density X = strong interaction parameter, M^v