JF12长实验时间激波风洞10°尖锥气动力实验研究  

Aerodynamic Force Measurements of 10° Half-Angle Cone in JF12 Long-Test-Time Shock Tunnel

作　　者：刘云峰[1,2] 汪运鹏[1,2] 苑朝凯[1,2] 罗长童[1,2] 姜宗林[1,2] LIU Yun-feng WANG Yun-peng YUAN Chao-kai LUO Chang-tong JIANG Zong-lin(State Key Laboratory of High-Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China School of Engineering Sciences, University of Chinese Academy of Sciences,Beijng 100049, China)

机构地区：[1]中国科学院力学研究所高温气体动力学国家重点实验室,北京100190 [2]中国科学院大学工程科学学院,北京100049

出　　处：《气体物理》2017年第2期1-7,共7页Physics of Gases

基　　金：国家自然科学基金(11672312;11532014)

摘　　要：介绍了在中国科学院力学研究所JF12长实验时间激波风洞上开展的10°尖锥标模的天平测力实验研究结果.JF12激波风洞的实验时间为100~130 ms,名义Mach数为7.0,喷管出口直径为2.5 m,总焓为2.5 MJ/kg,复现了35 km高空的飞行条件.采用六分量应变天平,攻角分别为-5,0,5,10和14°,模型长度为1.5 m,质量为50 kg.实验结果表明,在100~130 ms的实验时间里,应变天平的输出信号含有3~4个完整周期,可以通过对天平的输出信号进行平均直接获得气动力/矩测量结果,而不再需要进行加速度补偿,且气动力系数重复测量的不确定度小于2%.JF12激波风洞气动力系数的测量结果与传统高超声速风洞的结果符合得较好,表明在2.5 MJ/kg的总焓下,真实气体效应对该模型气动力特性的影响不明显.Aerodynamic force and moment measurements were conducted in JF12 long-test-time detonation-driven shock tunnel of Institute of Mechanics, Chinese Academy of Sciences. The test time of JF12 w,as 100 ？130 ms. The nominal Mach number was 7.0 and the exit diameter of the contoured nozzle was 2.5 m. The total enthalpy was 2.5 MJ/kg which duplicated the hypersonic flight conditions of 35 km altitude. The test model was standard aerodynamic model of 10° half-angle sharp cone. The length of the test model was 1500 mm with a mass of 50 kg. The aerodynamic forces were measured with a six- component strain balance. The angle of attack was set to be -5, 0, 5, 10 and 14°. The experimental results show that in the 100？130 ms test time, the signal of strain balance has 3 ？4 complete cycles. So the aerodynamic forces can be obtained directly by averaging the signal of balance without acceleration compensation. The uncertainty of force measurement in JF12 is less than 2%. The aerodynamic force coefficients of JF12 are in good agreement with that of conventional hypersonic wind tunnels with a difference of less than 2%. For this model under total enthalpy of 2.5 MJ/kg, the real-gas effects on aerody-namic force characteristics are not very evident.

关 键 词：JF12长实验时间激波风洞 高超声速气动力特性 10°尖锥标模 真实气体效应 

分 类 号：V211.22[航空宇航科学与技术—航空宇航推进理论与工程]