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A computational study of a scramjet combustor with swept ramp fuel injectors was conducted with the SPARK Navier -Stokes computer code. Turbulence was modeled with a two-zone algebraic turbulence model, while combustion was modeled with two nite rate H 2 -air chemistry models. The calculated reacting ow eld was mixing-limited. However, the extent of mixing was affected by the chemical reactions. Heat release from the chemical reactions signi cantly reduced the mixing between the fuel and airstreams. Comparisons between the calculations and experimental measurements of the wall pressure, surface heat ux, in-stream pitot pressure, as well as Mie scattering ow visualization were made and good overall agreement was observed. Nomenclature b j A T j = Arrhenius pre-exponential factor for the jth reaction c m T = eddy viscosity constant D = Damkohler number F = force G = gap, equals twice the duct height, 7.62 cm k f j = reaction rate coef cient for the jth reaction M = Mach number p = pressure T = temperature T a j = activation temperature for the jth reaction u = velocity component in the x direction V i = diffusion velocity of species i in the x direction w Ç i = chemical production rate of species i x, y, z = Cartesian coordinates P Y H O 2 = mass fraction of water caused by combustion I Z H = mass fraction of elemental hydrogen originating in the fuel jet Dt = time step ri = density of species i

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