Numerical simulation of ventral sting interference in high Reynolds number wind tunnel for civil aircraft low speed configuration

被引：0
|
作者：
Wang J. [1 ]
Gao Y. [1 ]
Jiao R. [2 ]
机构：
[1] Shanghai Aircraft Design and Research Institute, COMAC, Shanghai
[2] AVIC Aerodynamics Research Institute, Harbin
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2020年 / 41卷 / 04期
关键词：
Civil aircraft; High Reynolds number; Sting interference; Ventral sting; Wind tunnel test;
D O I：
10.7527/S1000-6893.2019.23526
中图分类号：
学科分类号：
摘要：
The wind tunnel to flight correlation correction is an important means to obtain the low-speed aerodynamic characteristics of modern civil aircraft. The method of increasing the wind tunnel test pressure is usually used to improve the Reynolds number, and the sting interference correction is a key part of the correction system. The numerical simulation is used to study the sting interference of the pressurized wind tunnel, and the variation of flow field and the main affected parts are analyzed. The comparison of the numerical simulation with the wind tunnel test shows that the lift coefficient differs by 0.006, the drag coefficient has a maximum difference of 0.001 2, and the pitching moment coefficient has a maximum difference of 0.01, verifying the reliability of the CFD numerical simulation method. The CFD simulation results show that the ventral sting increases the lift of the whole aircraft, reduces the drag, and increases the pitching moment. The ventral sting has a major influence on the lift of the wing. The ventral sting increases the dynamic pressure above the center of the wind tunnel and increases the flow velocity of the upper surface of the wing, thereby increasing the lift of the wing. Different from the traditional understanding, the ventral sting has a negative influence on the drag, and the main affected parts are slats because the deflection of the slats makes the normal vector part forward and reduces the drag. The main affected parts of the ventral sting on pitching moment are the fuselage and the horizontal tail. The results reveal the magnitude of the ventral sting on the aerodynamic characteristics, mainly affected parts, and the variation of flow fields. The results can provide reference for the correction of the sting interference and the optimization design of the support. The conclusion can be better used in the wind tunnel sting interference test and wind tunnel to flight data correction with certain engineering practicability. © 2020, Press of Chinese Journal of Aeronautics. All right reserved.
引用
收藏
相关论文
共 20 条
  • [1] Haines A.B., Scale effects on aircraft and weapon aerodynamics: AGARD-AG-323, (1994)
  • [2] Taylor G.S., Gursul I., Support interference for a maneuvering delta wing, Journal of Aircraft, 42, 6, pp. 1504-1515, (2005)
  • [3] Maina M., Corby N., Crocker E.L., Et al., A feasibility study on designing model support systems for a blended wing body configuration in a transonic wind tunnel, The Aeronautical Journal, 110, 1103, pp. 53-62, (2006)
  • [4] Zhong M., Zheng S., Wang G.L., Et al., Correlation analysis of combined and separatedeffects of wing deformation and support systemin the CAE-AVM study, Chinese Journal of Aeronautics, 31, 3, pp. 429-438, (2018)
  • [5] Hua J., Zheng S., Zhong M., Et al., Recent development of a CFD-wind tunnel correlation study based on CAE-AVM investigation, Chinese Journal of Aeronautics, 31, 3, pp. 419-428, (2018)
  • [6] Gebbink R., Wang G.L., Zhong M., High-speed wind tunnel test of the CAE aerodynamic validation model, Chinese Journal of Aeronautics, 31, 3, pp. 439-447, (2018)
  • [7] Eckert D., Hegen G.H., Kuhn W., DNW's method to correct for support and wall interference effects on low speed measurements with a large propeller powered transport aircraft model, 25th Congress of the International Council of the Aeronautical Sciences, pp. 994-1003, (2006)
  • [8] Kohzai M., Ueno M., Koga S., Et al., Wall and support interference corrections of NASA common research model wind tunnel tests in JAXA: AIAA-2013-0963, (2013)
  • [9] Kohzai M., Sudani N., Yamamoto K., Et al., Experimental and numerical studies of support interference in the JAXA 2 m×2 m transonic wind tunnel: AIAA-2010-4200, (2010)
  • [10] Ueno M., Kohzai T., Koga S., Et al., 80% scaled NASA common research model wind tunnel test of JAXA at relatively low Reynolds number: AIAA-2013-0493, (2013)
12