Airframe/Propulsion Integration is a key technology for air-breathing launch vehicle. This paper summaries the design constraints of RBCC (Rocket based Combined Cycle) power launch vehicle, and the performance of integration is evaluated by effective specific impulse which is a function of aerodynamic drag, engine thrust and specific impulse. The aerodynamic configuration of airframe/propulsion integration is designed, and analyzed by CFD. Considering the sizes of the vehicle are large, the inner channel is after the tip of the airframe to reduce the length of channel. Besides, the channel is behind the airframe to increase the aerodynamic lift, and the forebody is the outer compressed surface of the inlet. The analysis results show the lift-drag ratio can be up to 4.0 in subsonic and 3.5 in supersonic. The lift-drag ratio decreases when mach number is over 4. Finally, the design and analysis is verified by experiment of wind tunnel. The model of experiment is smaller than the origin configuration. The scale ratio is 77:1. The experiment is pressure test. The test results show the pressure configuration of launch vehicle which can guide the design of launch vehicle and verify the accuracy of CFD.
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