吸气式飞行器高超声速风洞气动力试验技术研究进展

摘要

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.%机体/推进一体化吸气式飞行器结构布局形式特殊, 为精确获得其气动力特性风洞试验数据, 必须发展可靠的风洞试验技术.针对一体化高超声速飞行器气动力风洞试验需求, 在中国空气动力研究与发展中心的高超声速风洞上发展了吸气式飞行器通气模型测力试验技术、尾喷流模拟测力试验技术、铰链力矩测量试验技术、通气模型动导数测量试验技术和飞行器表面摩阻测量试验技术, 为获得可靠的机体/推进一体化吸气式飞行器高超声速风洞气动力特性数据提供技术支撑.