高超声速通气模型直接测力试验  

Direct force measurement tests with hypersonic ducted model

作　　者：王泽江[1] 宋文萍[1] 曾学军[2] 杨波[2] 孙鹏[2] 唐小伟[2] WANG Zejiang SONG Wenping ZENG Xuejun YANG Bo SUN Peng TANG Xiaowei(School of Aeronautics, Northwestern Polytechnical University, Xi＇an 710072, China Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国空气动力研究与发展中心超高速空气动力研究所,绵阳621000

出　　处：《航空学报》2017年第10期25-32,共8页Acta Aeronautica et Astronautica Sinica

基　　金：国家"973"计划(2014CB744100);国家自然科学基金(11325212)~~

摘　　要：基于动量定理的内阻测量误差大,常规高超声速通气模型测力试验精度无法满足应用需求。为此,提出了采用"尾支+六分量天平"直接测量作用在通气模型机体控制体上的待测气动特性的新型试验方法,并对相关理论基础、工作原理进行了讨论。借鉴大尺度通气模型内外流解耦设计经验完成了模型设计,在FD-20A风洞上开展了原理性试验,通过对比分析来验证新型试验方法。结果表明:基于相似理论和力分解原则的通气模型直接测力试验方法可行,测量数据准确可信;试验数据信息丰富,能够准确评判间隙密封效果;由于减少了内阻测量环节,通气模型直接测力试验精度高;当来流马赫数为6时阻力系数误差小于2%,远低于常规通气模型测力试验,满足应用需求。Because of large errors of internal drag measurement based on the momentum theorem, the accuracy of Tradi- tional Force Test with Ducted Models （TFTDM） is unable to meet the demands at hypersonic speeds. To solve this problem, a new experimental method for Force Direct-Test with Ducted Models （FDTDM） is presented. The testing aerodynamic forces acting on the airframe control volume of ducted models with sting-supported model are measured directly by a six- component balance. The related theoretical basis and the working principle of FDTDM are discussed. The testing ducted model is designed using the design experience of large scale models with internal and external flow decoupling. A wind tunnel test is conducted in FD-20A hypersonic wind tunnel, and the methodology and technology of FDTDM are verified by compara- tive analysis. The results indicate that the new experimental method based on the similarity theory and the force decomposi- tion principles is feasible, and the measurements are accurate and credible. The information amount of experimental meas- urements is abundant, which could determine accurately the gas sealing effect. The accuracy of FDTDM is very high due to simplification of the procedure of internal drag measurement. The drag coefficient errors are less than 2% at free stream Mach number 6, which is far below that of TFTDM to meet the application requirements.

关 键 词：高超声速 风洞试验 直接测量方法 通气模型 天平 气动力 内阻 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]