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Nomenclature C = Chapman-Rubesin constant, /i w T ao /fj, ao T w e = specific internal energy E = total energy, e + (u 2 + v 2 )/2 k = coefficient of thermal conductivity M = Mach number p = pressure Pr = Prandtl number Re x = Reynolds number T = temperature T g = gas temperature at the wall u, v = velocity components in x, y directions v = rarefaction parameter, M QO (C/JR^j e )°' 5 x, y = distances along and normal to plate y = specific heat ratio by = Kronecker delta A = mean free path of the gasSubscripts t -total condition w = wall value oo = freestream value Theme T HE hypersonic rarefied flow near the sharp leading edge of a flat plate has been computed using a finite-difference solution of the complete, unsteady Navier-Stokes equations. The solution is advanced in time from the initial conditions until the steady-state solution is reached. The computational region extends from the freestream ahead of the plate to the stronginteraction regime. Both wall slip and temperature jump are included in the calculations. The numerical results compare favorably with experimental data and Monte Carlo simulations. In addition, it is shown for the first time that a numerical solution of the Navier-Stokes equations predicts that the wall pressure approaches the free-molecule limit at the leading edge.