Volume 32 Issue 5
Turn off MathJax
Article Contents
Abstract
References
Liu Litao, Jin Ling, Zhu Minghong, Li Shiwei, Jiang Kelin. 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. DOI: 10.11729/syltlx20180018
Citation: Liu Litao, Jin Ling, Zhu Minghong, Li Shiwei, Jiang Kelin. 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. DOI: 10.11729/syltlx20180018
shu

Numerical simulation of support interference and distortion effect on flying wing in low speed wind tunnel

  • Low Speed Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang Sichuan 621000, China

More Information
  • Received Date: February 08, 2018
  • Revised Date: August 02, 2018
    Graphical Abstract
    • Abstract
  • The flying wing configuration shows high aerodynamic efficiency and nice stealth performance. It represents the future military and civil aircraft development direction. The support interference and local shape deformation effect in the wind tunnel test are extremely complex. There are no general support program and correction method for the flying wing configuration test in the wind tunnel. This paper calculated the sting interference and after-body deformation effect on a calibration model of the small aspect ratio flying wing by numerical simulation method. By comparing with the test results, the numerical simulation results are found to be reasonable and the method is proved to be reliable. This method can be used in support program evaluation and support interference correction for the wind tunnel test. The longitudinal components of force or moment of the sting interference and after-body deformation effect are small compared to the longitudinal components themselves. The lateral-directional components of force or moment of the sting interference can be ignored. The lateral-directional components of force or moment of the after-body deformation effect and the lateral-directional components themselves are of the same order of magnitude.
    • FullText(HTML)
    • References (26)
  • [1]
    Cummings R M, Morton S A, Siegel S G, et al. Numerical prediction and wind tunnel experiment for a pitching unmanned combat air vehicle[R]. AIAA-2003-0417, 2003.
    [2]
    Petterson K. CFD analysis of the low-speed aerodynamic characteristics of a UCAV[R]. AIAA-2006-1259, 2006.
    [3]
    McParlin S C, Bruce R J, Hepworth A G, et al. Low speed wind tunnel tests on the 1303 UCAV concept[R]. AIAA-2006-2985, 2006.
    [4]
    Petterson K. Low-speed aerodynamic and flowfield characteristics of a UCAV[R]. AIAA-2006-2986, 2006.
    [5]
    Woolvin S J. A conceptual design study of the 1303 UCAV configuration[R]. AIAA-2006-2991, 2006.
    [6]
    Arthur M T, Petterson K. A computational study of the low-speed flow over the 1303 UCAV configuration[R]. AIAA-2007-4568, 2007.
    [7]
    Loser T, Vicroy D, Schütte A. SACCON static wind tunnel tests at DNW-NWB and 14'×22' NASA LaRC[R]. AIAA-2010-4393, 2010.
    [8]
    Vicroy D, Loser T. SACCON dynamic wind tunnel tests at DNW-NWB and 14'×22' NASA LaRC[R]. AIAA-2010-4394, 2010.
    [9]
    Gilliott A. Static and dynamic SACCON PIV tests, part Ⅰ: forward flowfield[R]. AIAA-2010-4395, 2010.
    [10]
    Konrath R, Roosenboom E, Schr der A, et al. Static and dynamic SACCON PIV tests, part Ⅱ: aft flow field[R]. AIAA-2010-4396, 2010.
    [11]
    Coton F, Mat S, Galbraith R. Low speed wind tunnel characterization of the VFE-2 wing[R]. AIAA-2008-0382, 2008.
    [12]
    Fritz W. Numerical simulation of the peculiar subsonic flow-field about the VFE-2 delta wing with rounded leading edge[R]. AIAA-2008-0393, 2008.
    [13]
    Carter M B, Dan D Vicroy. Blended-wing-body transonic aero-dynamics: summary of ground tests and sample results[R]. AIAA-2009-935, 2009.
    [14]
    Vicroy D D. Bended-wing-body low-speed flight dynamics: summary of ground tests and sample results[R]. AIAA-2009-933, 2009.
    [15]
    Liebeck R H. Design of the blended-wing-body subsonic transport[J]. Jouranl of Aircraft, 2004, 41(1):10-25. DOI: 10.2514/1.9084
    [16]
    Qin N, Vavalle A, Le Moigne A, et al. Aerodynamic studies for blended wing body aircraft[R]. AIAA-2002-5448, 2002.
    [17]
    程厚梅.风洞实验干扰与修正[M].北京:国防工业出版社, 2003.
    [18]
    王勋年.低速风洞试验[M].北京:国防工业出版社, 2002.
    [19]
    Carey G F, Stagg A K, Cline D D. Implementing a parabolized Navier-Stokes flow solver on massively parallel, scalable computer systems[C]//Proc of the 7th SIAM Conf on Parallel Processing for Scientific Commuting. 1990.
    [20]
    Kim S, Alonso J J, Jameson A. Mufti-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
    [21]
    Vav Muijden J. CFD support to wind tunnel experiments[C]//European Wind Tunnel Association 2nd Joint Workshop. Farnborough, 2006.
    [22]
    Mouton S. Numerical investigations of model support interference in subsonic and transonic wind tunnels[R]. ONERA, 2007.
    [23]
    李林, 马超, 王立新.小展弦比飞翼布局飞机稳定特性[J].航空学报, 2007, 28(6):1312-1317. DOI: 10.3321/j.issn:1000-6893.2007.06.006

    Li L, Ma C, Wang L X. Stability features of low aspect ratio flying wings[J]. Acta Aeronautica et Astronautica Sinica, 2007, 28(6):1312-1317. DOI: 10.3321/j.issn:1000-6893.2007.06.006
    [24]
    金玲, 刘李涛, 祝明红.小展弦比飞翼标模尾部畸变影响试验研究[J].空气动力学学报, 2016, 34(1):119-124. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601020

    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. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601020
    [25]
    衣秉立, 曾凯, 王世红.飞翼布局高速风洞尾支干扰试验修正技术研究[J].空气动力学学报, 2016, 34(1):98-106. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601017

    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. http://d.old.wanfangdata.com.cn/Periodical/kqdlxxb201601017
    [26]
    王勋年, 祝明红, 孙传宝.低速大迎角尾撑支架干扰试验研究[J].实验流体力学, 2007, 21(2):8-12. DOI: 10.3969/j.issn.1672-9897.2007.02.002

    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. DOI: 10.3969/j.issn.1672-9897.2007.02.002
    • Related Articles

  • Cited by

    Periodical cited type(1)

    1. 李强，操小龙. 超声速进气道压力估算方法及验证. 航空工程进展. 2020(06): 894-899 .

    Other cited types(0)

Catalog

    Get Citation
    PDF
    XML

    Article Metrics

    Article views (160) PDF downloads (8) Cited by(1)
    Related

    Submit Article

    Submission Guidelines

    Contact Us

    Qrcode

    Copyright © Editorial Department of Experimental Fluid Mechanics All Rights Reserved京ICP备14006930号-5

    Address: P. O. Box 11-9, 6 South Section of Second Ring Road, Mianyang, Sichuan 621000, China

    Tel: 0816-2463376 Email: syltlx@163.com

    Supported by: Beijing Renhe Information Technology Co., Ltd.  Baidu Analytics

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return
    x Close Forever Close