A theoretical analysis of the laminar base flow field of a two-dimensional reentry body has been formulated using Telenin's method. The numerical method divides the flow domain into horizontal strips along the x-axis and represents the flow variables as Lagrange interpolation polynomials in the vertical coordinate. The complete Navier-Stokes equations are used in the near wake region, and the boundary layer equations are applied elsewhere. The boundary conditions consist of the flat plate thermal boundary layer in the forebody region and the near wake profile in the downstream region. The resulting two-point boundary value problem of 33 ordinary differential equations is then solved by the multiple shooting method using 12 segments. The theoretical aspects of the convergence of the present scheme are discussed thoroughly and are compared to the successful convergence of a smaller system; i.e. the two-dimensional, two-phase stagnation point flow solution. The unsatisfactory convergence of the present study, which is attributed to two shortcoming in the formulation, can be improved if the following two steps are taken. First, a variable transformed coordinate should be incorporated to allow different stretching in various segments such that the instabilities encountered can be avoided. Secondly, the Lagrange interpolation polynomials should be replaced by other forms of polynomials or analytic functions to remove the mathematical singularity at the rear stagnation point. The specific case considered in this report is that of vehicle reentry at zero angle of attack in a Mach 11 free stream with Reynolds number Re ∞, H ranging from 0.8 × 10 5 to 1.2 × 10 5. The base wall temperature remains constant at 255°K (460° R) and the free stream temperature is 217.43° K (392.28° R). It was assumed that heat conductivity and viscosity are linearly proportional to temperature, the specific heat is constant, and the Prandtl number is unity. The detailed flow field and thermal environment in the base region are presented in the form of temperature contours, Mach number contours, velocity vectors, pressure distributions, and heat transfer coefficients on the base surface. The maximum heating rate was found to be always on the centerline, and the two-dimensional stagnation point flow solution was adequate to estimate this value as long as the local Reynolds number could be obtained.