通气模型内流道阻力直接测量技术  

Technique Investigation on Flow-Through Model Inner-Flow Drag Straightway Measured by Strain-Gauge Balance

作　　者：许晓斌[1,2] 舒海峰[1] 谢飞[1] 张德炜[1] 

机构地区：[1]中国空气动力研究与发展中心超高速所,四川绵阳621000 [2]中国空气动力研究与发展中心高超声速冲压发动机技术国防科技重点实验室,四川绵阳621000

出　　处：《推进技术》2013年第3期311-315,共5页Journal of Propulsion Technology

摘　　要：推阻特性是吸气式飞行器研制中最为关注的气动特性问题之一。为研究通气模型内流道阻力特性,在中国空气动力研究与发展中心(CARDC)超高速所的1m高超声速风洞上开展了吸气式飞行器通气模型内流道阻力直接测量技术研究。研究选取吸气式飞行器的一个内流道模块为研究对象,通过将内流道模块与模型其余部分进行分离设计、采用特种应变天平直接测量模型内流道气动力的方法得到通气模型内阻,同时进行了干扰因素分析和试验数据修正方法研究,开展了Ma=4条件下的内流道阻力测量试验并给出了典型试验结果。试验结果表明,通气模型内阻随攻角和喉道高度变化而变化。The thrust-drag characteristic is important to the design of airbreathing vehicle.A wind tunnel experimental technique investigation was studied to measure the inner drag of flow-though model in 1m wind tunnel of China Aerodynamics Research and Development Center.The inner flow passage of an airbreathing vehicle was separated from other parts of the model to measure the inner aerodynamic force with a specially designed strain-gauge balance.The error factors which may affect the test result precision were discussed,along with test data correction methods.A wind tunnel test was conducted at Ma=4,and the test results indicate that the inner flow drag varies with the angle of attack and throat size of the inlet.

关 键 词：吸气式飞行器 通气模型 内流道 阻力 风洞试验 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]