Numerical simulation investigation of aerodynamic interference of sting support in wind tunnel test of a delta wing at big angles of attack

被引：0
|
作者：
Zhang J. [1 ]
Ai Y. [2 ]
Huang D. [1 ]
Liu J. [3 ]
机构：
[1] College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] Second Research Room, Jiangnan Mechanical & Electrical Design Institute, Guiyang
[3] Keppel-NUS Corporate Laboratory, Singapore City
来源：
Zhang, Jun (zhangjunrdf@nuaa.edu.cn) | 1600年 / Chinese Society of Astronautics卷 / 37期
基金：
中国国家自然科学基金;
关键词：
Delta wing; High angle of attack; Large eddy simulation; OpenFOAM; SA-DDES; Unsteady flow field;
D O I：
10.7527/S1000-6893.2016.0095
中图分类号：
学科分类号：
摘要：
In current wars, the fighter is required to be capable of stalled flight at a high angle of attack (AOA). The investigation of the aerodynamic characteristics of the aircraft mainly relies on wind tunnel test and numerical simulation. In the wind tunnel test of high angle of attack, the commonly used method is to use sting support. The presence of the sting support can have an effect on the model testing results which will be numerically investigated in the present paper. The open source software package OpenFOAM 2.3 is used as computational fluid dynamics (CFD) computing platform, the PIMPLE algorithm is applied to solving Navier-Stokes (N-S) equations. The PIMPLE algorithm is a combination of both semi-implicit method for pressure-linked equations (SIMPLE) and pressure implicit with splitting of operator (PISO). A finite volume method is used for spatial discretization. Second order linear interpolation is also adopted. Backward differentiation method is to deal with time discretization. The employed turbulence model is Spalart-Allmaras-delayed detached eddy simulation (SA-DDES). In order to verify the reliability of the numerical method, the flow filed of the delta wing with sting support is computed at angles of attack of 0°, 10°, 30°, 50°, 70°, and 90° firstly. The obtained results are compared to the testing data and they are in close agreement. After that, the numerical simulation of the flow field of the delta wing without sting support is executed. The influence of the sting support on the flow filed, pressure coefficient distribution on the leeward side and aerodynamic coefficient is obtained through comparing the numerical results with and without sting support. In contrast to the situation without the sting support, at a high angle of attack, the presence of the sting support affects the flow field around the delta wing (but does not change the vortices and flow structure) and alters the pressure coefficient distribution on the wing leeward side. Therefore, normal force and pitching moment coefficients have significant changes. © 2016, Press of Chinese Journal of Aeronautics. All right reserved.
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页码：2481 / 2489
页数：8
相关论文
共 24 条
  • [1] Chen H.M., Interference and Correction in Wind Tunnel Experiment, (2003)
  • [2] Wang X.N., Zhu M.H., Sun C.B., Investigation on the interference of rear sting supports at high angle of attack in low speed wind-tunnel, Journal of Experiments in Fluid Mechanics, 21, 2, pp. 8-12, (2007)
  • [3] Zhu M.H., Sun H.S., Jin L., Et al., Study on the support interference of wire-assistant sting support at high angle of attack in low speed wind tunnel, Journal of Experiments in Fluid Mechanics, 25, 3, pp. 1-5, (2011)
  • [4] Su J.C., Huang Y., Li Y.H., Et al., Support interference of low-aspect-ratio flying-wing from subsonic to supersonic speed, Acta Aerodynamica Sinica, 33, 3, pp. 289-295, (2015)
  • [5] Yang X.W., Liu X., Support form and support interference on transport aircraft model in high speed wind tunnel, Acta Aerodynamica Sinica, 33, 6, pp. 721-727, (2015)
  • [6] Tang M.Z., Li Z.F., Yu W.Y., Et al., Experimental study on aerodynamic characteristics of delta wing at low speed and high angle of attack, Acta Aerodynamica Sinica, 12, 4, pp. 367-374, (1994)
  • [7] Zhang W.H., Li Z.Q., Ding K.W., Et al., Unsteady wall corrections for a delta wing oscillating in pitch to very high angles of attack, Acta Aeronautica et Astronautica Sinica, 18, 2, pp. 215-219, (1997)
  • [8] Huang D., Li Z.Q., Ding K.W., Et al., Wall interference in unsteady force tests for delta wing in large amplitude pitching motions, Journal of Nanjing University of Aeronautics & Astronautics, 35, 1, pp. 13-17, (2003)
  • [9] Sun H.S., Jiang Y.B., Liu Z.T., Et al., Experimental research on the high angle of attack aerodynamic characteristics of an 80°/65° double-delta wing, Journal of Experiments in Fluid Mechanics, 25, 6, pp. 6-12, (2011)
  • [10] Tao Y., Zhao Z.L., Li H., Et al., Investigation on dynamic behavior forecast of 80°/65° double-delta wing in roll at high incidence, Journal of Experiments in Fluid Mechanics, 6, pp. 43-46, (2013)
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