为研究半球形多孔探针在超声速大气条件下产生脱体激波的形状和脱体距离随马赫数变化规律,采用CFD方法模拟大气环境,在1.2～1.7马赫数范围内进行数值仿真实验,用双曲线激波形状展示法和最小二乘法拟合得到了激波曲线离心率、脱体距离、曲率半径与马赫数间的函数关系,建立了脱体激波曲线参数化方程。将参数化方程与仿真结果和经验公式比较,结果证明,该参数化方程与仿真结果极为相符,且在距离球体较近处精度较高。参数化方程与经验公式预测的脱体距离差值不超过球体半径的5%。
Abstract
In order to study the change law of the shape and standoff distance of the shock wave for hemispherical porous probe under supersonic atmospheric conditions, when the Mach number changes. CFD method was used to simulate the atmospheric environment, and numerical simulation experiments were carried out in the range of 1.2～1.7 Mach number. Hyperbola was used to represent the detached shock wave, and the functional relationship between the curvature, the standoff distance, the directrix distance of the shock wave and the Mach number was fitted by the least square method, and the parametric equation of the detached shock wave curve was established. The parametric equation is compared with the simulation results and the empirical formula, and the results show that the parametric equation is in good agreement with the simulation results, and the accuracy is higher when the distance is closer to the sphere. The difference between the distance predicted by the parametric equation and the empirical formula does not exceed 5% of the sphere radius.
关键词
计量学 /
大气三维流场探测 /
半球形多孔探针 /
超声速 /
脱体激波 /
数值仿真
Key words
metrology /
atmospheric three-dimensional flow field detection /
hemispherical multi-hole porous probe /
supersonic /
detached shock wave /
numerical simulation
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参考文献
［1］Crowley C, Shinder I I, Moldover M R. The effect of turbulence on a multi-hole Pitot calibration［J］. Flow Measurement and Instrumentation, 2013, 33: 106-109.
［2］Telionis D, Yang Y, Rediniotis O. Recent developments in multi-hole probe (MHP) technology［C］// COBEM. 20th International Congress of Mechanical Engineering,Gramado, RS, Brazil. 2009.
［3］Shaw-Ward S, Titchmarsh A, Birch D M. Calibration and use of n-hole velocity probes［J］. AIAA Journal, 2015, 53(2): 336-346.
［4］Wildmann N, Ravi S, Bange J. Towards higher accuracy and better frequency response with standard multi-hole probes in turbulence measurement with remotely piloted aircraft (RPA)［J］. Atmospheric Measurement Techniques, 2014, 7(4): 1027-1041.
［5］Lukasiewicz J. Blast-hypersonic flow analogy theory and application［J］. American Rocket Society Journal, 1962, 32(9): 1341-1346.
［6］Maslen S H. Inviscid hypersonic flow past smooth symmetric bodies［J］. AIAA Journal, 1964, 2(6): 1055-1061.
［7］Cheng H K, Gaitatzes G A. Use of the shock-layer approximation in the inverse hypersonic blunt body problem［J］. AIAA Journal, 1966, 4(3): 406-413.
［8］Inouye M. Shock standoff distance for equilibrium flow around hemispheres obtained from numerical calculations［J］. AIAA Journal, 1965, 3(1): 172-173.
［9］董维中. 气体模型对高超声速再入钝体气动参数计算影响的研究［J］. 空气动力学学报, 2001, 19(2): 197-202.
Dong W Z. Study on the effects of gas models on the calculation of pneumatic parameters of hypersonic re-entry into the blunt body［J］. Journal of Aerodynamics, 2001, 19 (2): 197-202.
［10］王偲臣, 杜娟, 李帆, 等. 一种动态五孔探针: CN107101798B［P］. 2019-01-18.
［11］Lynn J F. Multigrid solution of the Euler equations with local preconditioning［D］. Ann Arbor: University of Michigan, AAI9542898, 1995.
［12］Anderson Jr J D. Fundamentals of aerodynamics, Sixth edition［M］. New York: Tata McGraw-Hill Education, 2010: 584-587.
［13］王卫国, 樊雯璇, 吴涧, 等. 全球对流层顶气压场和温度场的时空演变结构特征［J］. 云南大学学报(自然科学版), 2006, 28(2): 127-135, 177.
Wang W G, Fan W X, Wu J, et al. The structural characteristics of the evolution of space-time in the top pressure field and temperature field of the global esosphere［J］. Journal of Yunnan University(edition of natural science), 2006, 28(2): 127-135, 177.
［14］郑之初. 跨音速下圆球脱体激波［J］. 空气动力学学报, 1984, 2(3): 98-103.
Zheng Z C. Transonic ball detached shock wave［J］. Journal of Aerodynamics, 1984, 2(3): 98-103.
［15］Billig F S. Shock-wave shapes around spherical-and cylindrical-nosed bodies［J］. Journal of Spacecraft and Rockets, 1967, 4(6): 822-823.
基金
国家自然科学基金(41775039,41775165)
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