Nozzle chemical non-equilibrium effects based on strut combustor

The finite volume method in implicit scheme and surrogate fuel C₁₂H₂₃'s 10 species and 13 step reactions Arrhenius finite-rate model were adopted to investigate the non-equilibrium chemical reaction flow in kerosene-fueled scramjet single expansion ramp nozzle (SERN), and the 'inlet thin layer' problem in SERN model was effectually solved by establishing the strut combustor-SERN model. Numerical simulation results show that the chemical non-equilibrium effect exits in the whole SERN, especially near the nozzle inlet zone; The SERN performance with non-equilibrium chemical reaction flow is obviously higher than that with frozen flow. With the increase of engine equivalent mixture ratio (ε) the δ grows up, which is the percentage of increment about nozzle thrust coefficient and lift coefficient with non-equilibrium chemical reaction flow relative to frozen flow. When the ε=0.8, thrust coefficient increment δ_CF=9.41%, lift coefficient increment δ_CY=16.39%, thus the chemical non-equilibrium effect of kerosene-fueled scramjet nozzle cannot be ignored.