A two-dimensional model has been developed to study the flame structure above composite propellants using a vorticity-velocity formulation of the transport equations. This formulation allows for a more stable, robust, accurate, and faster solution method compared with the compressible Navier-Stokes equations in the low Mach flow regime. The model includes mass and energy coupling between the condensed and gas phases. The condensed-phase model is based on previously reported one-dimensional models and includes distributed decomposition and multistepreaction kinetics. The model uses a detailed gas-phase kinetic mechanism consisting of 37 species and 127 reactions. The kinetic mechanism and species diffusion determine the flame structure of the system; no assumptions are made beforehand, aside from appropriate boundary conditions. Numerical studies have been performed to examine the flame structure above an ammonium-perchlorate/hydroxy-terminated-polybutadiene propellant. The predicted flame structure was found to be qualitatively similar to the Beckstead-Derr-Price model with both premixed and diffusion flames present. Results present significant insight into ammonium perchlorate's ability to control a propellant's burning rate and illustrate the importance of the primary diffusion flame in composite propellant combustion.Nomenclature c p = heat capacity, erg=g=K g = gravitational acceleration vector, cm=s 2 h = specific enthalpy, erg=g i = species index M = Mach number r = radial distance, cm r = radial direction T = temperature, K t = time, s v = velocity vector, cm=ŝ v = diffusion velocity, cm=s W = molecular mass, g=mol _ w = chemical production rate, g=cm 3 =s Y = mass fraction z = axial direction = thermal conductivity, erg=s=cm=K = viscosity, poise = density, g=cm 3 = dissipation function ! = vorticity vector, 1=s