Investigation of equivalence ratio effect on kerosene-fueled low internal drag scramjet combustor performance

Numerical simulations of 3D non-reacting and reacting flows in a kerosene-fueled Scramjet combustor that corresponds to a direct-connect experimental facility by CAAA have been carried out to investigate the nature of mixing and combustion in this configuration. The fuel is assumed to be gaseous for computational efficiency. The combustor entry Mach number is nominally 2.5. Details of the flow field inside the combustor, such as contours of static pressure, static temperature, species mass fraction, and Mach number, are discussed. Also, the variation of metrics such as mixing efficiency, combustion efficiency, and integrated flow momentum along the length of the combustor, are presented. Predicted values of wall static pressure along the bottom wall of the combustor are compared with previously reported experimental data. The calculations underpredict the pressure rise, but the overall pressure rise trend is predicted well. © 2011 by China Academy of Aerospace Aerodynamics.