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Abstract
The combustion of a solid fuel under supersonic cross flow conditions was investigated theoretically. A two-dimensional, axisymmetric, turbulent ( k– ε), two-reaction, six-species reactive flow model was developed and solved numerically. The nominal case investigated simulated stagnation conditions resulting from flight Mach number of 5 at 15 km for a designed combustor entrance Mach number of 1.5. The results demonstrate the feasibility of solid fuel combustion under supersonic cross flow where the diffusion flame supplies a substantial heat addition to the flow. The sensitivity of the combustor performance to flight Mach number, combustor inlet Mach number, combustor size, step size and length of fuel grain was studied. The effects on flow pattern, regression rate profiles as well as flame temperature and location were evaluated. Typical computed combustion efficiencies of the order of 0.7–0.9 support potential use of solid fuel scramjet.
Published Version
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