Abstract: To get accurate wind tunnel test results with high precision for the airframe/propulsion integrated air-breathing hypersonic flight vehicles, reliable wind tunnel test techniques must be developed according to the vehicle's special configuration and structure. To satisfy the requirements of hypersonic wind tunnel tests for those airframe/propulsion integrated vehicles, the flow-through model aerodynamic force measurement technique, rear-jet interference test technique, hinge-moment measurement technique, flow-through model dynamic derivative test technique, and the surface skin-friction measurement technique have been developed in hypersonic wind tunnels of CARDC(China Aerodynamics Research and Development Center), which give massive support to those efforts to get authentic hypersonic wind tunnel test results for the design and evaluation of airframe/propulsion integrated air-breathing hypersonic flight vehicles.