Experiment of far-field interference of cantilever support device  in 8 m × 6 m low speed wind tunnel

LIU Litao; HUANG Zhiyuan; CHEN Hong; FAN Litao; LI Xiaobing; LIU Yan

doi:10.7638/kqdlxxb-2022.0110

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Experiment of far-field interference of cantilever support device in 8 m × 6 m low speed wind tunnel

更新时间：2026-05-28

- Experiment of far-field interference of cantilever support device in 8 m × 6 m low speed wind tunnel
- Vol. 41, Issue 7, Pages: 102-111(2023)
- 作者机构：
  
  中国空气动力研究与发展中心低速空气动力研究所,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0110
  CLC： V211.7
- Published：2023
- 稿件说明：
移动端阅览
刘李涛, 黄志远, 陈洪, 等. 8 m × 6 m低速风洞悬臂支撑机构远场干扰试验[J]. 空气动力学学报, 2023, 41(7): 102−111.

LIU Litao, HUANG Zhiyuan, CHEN Hong, et al. Experiment of far-field interference of cantilever support device in 8 m × 6 m low speed wind tunnel[J]. 2023, 41(7): 102-111.
刘李涛, 黄志远, 陈洪, 等. 8 m × 6 m低速风洞悬臂支撑机构远场干扰试验[J]. 空气动力学学报, 2023, 41(7): 102−111. DOI： 10.7638/kqdlxxb-2022.0110

LIU Litao, HUANG Zhiyuan, CHEN Hong, et al. Experiment of far-field interference of cantilever support device in 8 m × 6 m low speed wind tunnel[J]. 2023, 41(7): 102-111. DOI： 10.7638/kqdlxxb-2022.0110.

摘要

8 m × 6 m低速风洞悬臂支撑机构是风洞主力支撑装置，其对试验模型的气动干扰可分为近场干扰和远场干扰（主要为悬臂干扰）两部分，采用两步法进行的支撑干扰试验一般仅获取近场干扰量，而获取远场干扰量则较为复杂，普遍对其进行了忽略。本文在8 m × 6 m低速风洞采用流场测量和典型模型测力试验方法对悬臂支撑机构远场（悬臂）干扰进行了研究，获得了较为可靠的悬臂干扰特性，并建立了基本修正方法，可为后续8 m × 6 m低速风洞悬臂支撑机构远场干扰通用修正方法的建立和验证提供数据支撑。

Abstract

The cantilever support device is one of the most commonly used support devices in the 8 m × 6 m low-speed wind tunnel. However

it inevitably exerts aerodynamic interference on the test model

which can be divided into near-field and far-field interferences. Correction of the aerodynamic interference is indispensable for obtaining reliable aerodynamic performance of testing models. The two-step method is commonly used in conventional support interference tests

where only the near-field interference is usually obtained

but the far-field interference is difficult to acquire. In this paper

the aerodynamic interference of the cantilever support device is studied by flow field and force measurement of typical models in the 8 m × 6 m low speed wind tunnel (FL-13) of China Aerodynamic Research and Development Center. Based on analyses of the interference characteristics of the cantilever support device

we propose an effective method for correcting the support interference. These results provide valuable support for developing and verifying the far-field interference correction methods in the 8 m × 6 m low speed wind tunnel.

关键词

Keywords

references

CHENG H M. Interference and correction on wind tunnel testing[M]. Beijing: National Defense Industry Press, 2003 (in Chinese).

王勋年. 低速风洞试验[M]. 北京: 国防工业出版社, 2002: 324.

CAREY G F, STAGG A K, CLINE D D. Implementing a parabolized Navier-Stokes flow solver on massively parallel, scalable computer systems[C] // 7th SIAM Conf. on Parallel Processing for Scientific Commuting, 1990.

KIM S, ALONSO J J, JAMESON A. Multi-element high-lift configuration design optimization using viscous continuous adjoint method[J]. Journal of Aircraft, 2004, 41(5): 1082-1097. DOI:10.2514/1.17

VAV MUIJDEN J. CFD support to wind tunnel experiments[C]//European Wind Tunnel Association 2nd Joint Workshop, Farnborough, 2006.

MOUTON S. Numerical investigations of model support interference in subsonic and transonic wind tunnels[R]. ONERA 2007.

GARCIA J A, MELTON J, SCHUH M J, et al. NASA ERA integrated CFD for wind tunnel testing of hybrid wing-body configuration (invited)[C]// 54th AIAA Aerospace Sciences Meeting, San Diego, California, USA. Reston, Virginia: AIAA, 2016. doi: 10.2514/6.2016-0262

BAI F, HU Y. Research of low-speed wind tunnel ventral support interfere[J]. Civil Aircarft Design Research, 2012(4): 33-34, 39. (in Chinese)

LIU L T, JIN L, ZHU M H, et al. Numerical simulation of support interference and distortion effect on flying wing in low speed wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2018, 32(5): 54-60. (in Chinese)

JIN L, LIU L T, ZHU M H, et al. Study on the distortion effect of flying wing in low speed wind tunnel[J]. Acta Aerodynamica Sinica, 2016, 34(1): 119-124. (in Chinese)

YI B L, ZENG K, WANG S H. Investigation on the interference correction of flying wing aircraft rear sting support in high speed wind tunnel test[J]. Acta Aerodynamica Sinica, 2016, 34(1): 98-106. (in Chinese)

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[J]. Journal of Experiments in Fluid Mechanics, 2007, 21(2): 8-12. (in Chinese)

ECKERT D. Correction of support influences on measurements with sting mounted wind tunnel models[C] // Proc of the AGARD Meeting on Wall Interference, Support Interference and Flow Field Measurements. 1993.

YU Y G, ZHOU Z, HUANG J T, et al. Aerodynamic design of a standard model CHN-T1for single-aisle passenger aircraft[J]. Acta Aerodynamica Sinica, 2018, 36(3): 505-513. (in Chinese)

FAN L T, DUAN X F, XUE W. Advances in test techniques based on multifunctional sting support system for 8m × 6m wind tunnel[J]. Applied Mechanics and Materials, 2013, 336-338: 880-884. DOI:10.4028/www.scientific.net/amm.336-338.880

ZHANG H, FAN L T. Correlation analysis of large low speed wind tunnel test on CHN-T1 calibration model[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(3): 106-111. (in Chinese)

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Progress and prospect on Reynolds number effects of advanced aircraft

The calibration of of the Φ3 m high temperature tunnel performance

Numerical simulation on gust responses of high aspect ratio aircraft

Optimization of hot-air anti-icing structures based on neural networks and genetic algorithms

Multi-factor analysis and simulation of particle erosion characteristics of fan blades

Related Author

WU Jifei

KONG Wenjie

LI Guoshuai

TIAN Shuling

TANG Zhigong

CHEN Dejiang

ZHU Chao

ZENG Lingguo

Related Institution

High Speed Aerodynamic Research Institute of China Aerodynamic Research and Development Center, Mianyang

College of Aerospace Engineering, Nanjing University of Aeronautics And Astronautics, Nanjing

Hypervelocity Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang

AI问答

⁰