Because of the excellent performance and great potentiality at hypersonic range, scramjet engineis becoming the most promising and attractive thruster for next generation hypersonic aircraft. Therefore, the related technologies of scramjet and scramjet -powered hypersonic aircraft were intensively developed all over the world in the past decades. One of the keys for the success of airbreathing hypersonic aircraft is the effective integration design of airbreathing scramjet engine with the airframe. The integrated propulsive flowpath of scramjet configuration was preliminarily designed and analyzed in this paper. The flow-fields characteristics and performance of the designed two-dimensional integrated propulsive flowpath were numerically calculated with various equivalent fuel-air ratio conditions, using computational fluid dynamics methods. The calculation results were then compared with the experimental data at some typical conditions, and the flow-field and performance of the integrated scramjet flowpath with different equivalent fuel-air ratio were analyzed and discussed in detail. The investigation results from this efforts show that: (1)The three oblique shock waves of forebody/inlet compression are well attached to the inlet cowl-lip at the design point flight Mach of 6.0; (2)The inlet function is beyond of disturbing by combustion induced shock wave and pressure fluctuations under the equivalent fuel-air ratio condition of 1. 0, which is well-satisfied to the design requirements; (3)With the increasing equivalent fuel-air ratio, the combustion intensity in the combustor is significantly enhanced, resulting in a increasing net-thrust of the propulsive flowpath.
