Φ3 m高温风洞流场性能校准  

The calibration of of theΦ3 m high temperature tunnel performance

作　　者：唐志共[1] 陈德江[1] 朱超[1] 曾令国[1] 吴锦水 TANG Zhigong;CHEN Dejiang;ZHU Chao;ZENG Lingguo;WU Jinshui(Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center,Mianyang 710072,China)

机构地区：[1]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：《空气动力学学报》2023年第11期28-35,I0001,共9页Acta Aerodynamica Sinica

摘　　要：中国空气动力研究与发展中心Φ3 m高温风洞是新建成的3米量级暂冲型、自由射流式高温风洞,采用空气/液氧/异丁烷三组元燃烧加热产生高压高温高速气体和真空抽吸联合运行。为评估该高温风洞流场性能,开展了风洞调试和流场校测试验。试验结果表明:风洞可模拟马赫数4~7、高度17~30 km飞行条件下的马赫数、动压、总焓、氧组分、时间等参数,最高总温2335 K;风洞流场品质好、均匀区尺寸大,喷管出口均匀区尺寸达到喷管出口直径的80%以上,均匀区内马赫数和总温偏差均优于2%;流向马赫数菱形均匀区大于理论预测值,流向总温均匀区呈直筒形分布;风洞长时间运行时流场参数波动小,马赫数和总温波动均优于2%。风洞具备了开展高速飞行器空气动力学、推进、材料与结构等试验研究的能力。TheΦ3 m high temperature wind tunnel of China Aerodynamics Research and Development Center is a 3-meter-scale free-jet wind tunnel built recently in China,which is used to conduct aero-thermal loads,aero-thermo-structures,high-enthalpy aerodynamics research and air-breathing propulsion systems testing at different total enthalpy conditions which are conformed to the realistic flight environment.The high-enthalpy flow is produced by burning isobutene,liquid oxygen and air in the combustor,and then goes through the expansion section of nozzle,passes the test section in which the flow is uniform.In the downstream of test section,the flow is exhausted by the diffuser and then arrives at vacuum tank.In order to evaluate the wind tunnel performance,a series of flow field calibration tests were conducted within Mach numbers 4~7.The results indicate that the diameter of uniform flow area is more than 80%of nozzle outlet diameter.In the test section in which the flow is uniform,the deviation of the Mach number and total temperature of flow are within two percent of the average Mach number and total temperature respectively.The tunnel has the ability to simulate Mach number,dynamic pressure,total enthalpy,oxygen components and flight time at Mach numbers of 4~7 and altitudes of 17~30 kilometers.The highest total temperature of flow is 2335 K.The flow field is very stable during long-time operation.The maximum fluctuation of Mach number and total temperature is no more than 2%.The HHT will carry out aerodynamic,propulsion,materials and structures evaluation tests of hypersonic aircraft in the future.

关 键 词：高温风洞 试验 流场品质 流场校测 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]