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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.
In this paper, the results of the balance force test of 10 ° cone model carried out on JF12 wind tunnel with long experimental time of the Institute of Mechanics, Chinese Academy of Sciences are introduced. The experiment time of wind tunnel of JF12 shock is 100-130 ms, Of 7.0, nozzle outlet diameter of 2.5 m, total enthalpy of 2.5 MJ / kg, reproduce the flight conditions of 35 km altitude using a six-component strain gauge, angle of attack were -5,0,5,10 and 14 ° , The length of the model is 1.5 m and the mass is 50 kg.The experimental results show that the output signal of the strain gage contains 3 to 4 complete cycles in the experiment period of 100 to 130 ms and can be directly obtained by averaging the output signals of the balance Aerodynamic force / moment measurement without acceleration compensation, and the uncertainty of aerodynamic coefficient repeated measurement is less than 2%. The measurement results of aerodynamic coefficient of JF12 shock wind tunnel are consistent with those of conventional hypersonic wind tunnel It is better that the real gas effect has no obvious effect on the aerodynamic characteristics of the model at a total enthalpy of 2.5 MJ / kg.