An implicit Navier-Stokes solver has been developed for simulating the steady laminar supersonic flow past a semi-infinite flat plate at zero incidence. The implicit finite difference technique of Beam and Warming is employed for solving the two-dimensional compressible Navier-Stokes equations. Computations have been carried out for the test case of Mach number = 2.0 and .6. Reynolds number = 10. The velocity profile in the boundary layer compares well w:ith the similar solution profile. The 2-D Navier-Stokes code is capable of capturing the leading edge shock as well. About 300 time steps are needed to yield the time asymptotic steady state solution
