Integrated flow field calculation of a modularized scramjet

An integrated scramjet flow field was numerically investigated using multi-species Navier-Stokes equations with finite rate chemistry. The Lower-Upper (LU) decomposition method was used to integrate the NS equations in time while the MUSCL type upwind scheme in space. The performances of the scramjet, including thrust coefficient, drag coefficient, lift coefficient and specific impulse were obtained from the computational results. Scramjet performances under different attack angles and gas-fuel equivalence ratios were studied, and the influence of inlet side compression on scramjet performances was investigated. It is shown that the codes developed in this work can be used to simulate the integrated flow field of scramjet. Some suggestions were given to improve the scramjet design model.