Experimental study on side force alleviation of conical forebody with a fluttering flag

被引:13
|
作者
Zhang, Weiwei [1 ]
Liu, Xiaobo [1 ]
Zhai, Jian [1 ]
Ye, Zhengyin [1 ]
机构
[1] Northwestern Polytech Univ, Natl Key Lab Aerodynam Design & Res, Xian 710072, Peoples R China
关键词
BODIES; VORTICES; FLOW; STABILITY;
D O I
10.1063/1.4772201
中图分类号
O3 [力学];
学科分类号
08 ; 0801 ;
摘要
Slender bodies of revolution placed at high angles of attack will produce a steady asymmetric vortex pair. This behavior is determined by the spatial instability of the flow. The asymmetric vortex pair is very sensitive to small disturbances near the tip. This paper presents a simple side force alleviation method without a power unit for slender bodies at high angles of attack. The method uses the self-excited oscillation (flutter) of a small cantilever flag as the excitation source on the cone tip. An experimental study is performed to investigate the characteristics of the asymmetric side forces of a 20 degrees cone-cylinder slender body with and without a small flutter flag. Pressure distribution at eight cross sections of the cone forebody is measured at different free-stream velocities and different angles of attack. The process demonstrates that the excitation provided by the fluttering flag can change the asymmetric bistable flow state to a well symmetric one at high angles of attack, and that the corresponding side force and yaw moment will significantly decrease. The flutter strength of the flag will be enhanced by increasing the free-stream velocity. The effectiveness of the side force alleviation method will also be increased. (C) 2012 American Institute of Physics. [http://dx.doi.org/10.1063/1.4772201]
引用
收藏
页数:11
相关论文
共 50 条
  • [1] Approach to side force alleviation through modification of the pointed forebody geometry
    Modi, V.J.
    Stewart, A.C.
    Journal of Aircraft, 1992, 29 (01): : 123 - 130
  • [2] APPROACH TO SIDE FORCE ALLEVIATION THROUGH MODIFICATION OF THE POINTED FOREBODY GEOMETRY
    MODI, VJ
    STEWART, AC
    JOURNAL OF AIRCRAFT, 1992, 29 (01): : 123 - 130
  • [3] Experimental study on the thermal-hydraulic performance of a fluttering split flag in a channel flow
    Zhong, X. L.
    Fu, S. C.
    Chan, K. C.
    Yang, G.
    Qiu, H. H.
    Chao, Christopher Y. H.
    INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER, 2022, 182
  • [4] Influence of sweep wings on side force of forebody of a slender
    Li, Guo-Hui
    Wang, Gang
    Deng, Xue-Ying
    Shiyan Liuti Lixue/Journal of Experiments in Fluid Mechanics, 2007, 21 (04): : 7 - 12
  • [5] Experimental study of dynamic conical ice force
    Xu, Ning
    Yue, Qianjin
    Bi, Xiangjun
    Tuomo, Karna
    Zhang, Dayong
    COLD REGIONS SCIENCE AND TECHNOLOGY, 2015, 120 : 21 - 29
  • [6] Experimental Investigation of Wing Rock Phenomenon of a Fighter Aircraft with Conical Forebody
    Hyoung-Seog Chung
    Donghyurn Cho
    Jongbum Kim
    Young Il Jang
    International Journal of Aeronautical and Space Sciences, 2021, 22 : 303 - 317
  • [7] Experimental Investigation of Wing Rock Phenomenon of a Fighter Aircraft with Conical Forebody
    Chung, Hyoung-Seog
    Cho, Donghyurn
    Kim, Jongbum
    Jang, Young Il
    INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES, 2021, 22 (02) : 303 - 317
  • [8] SIDE-FORCE CONTROL ON A DIAMOND FOREBODY AT HIGH ANGLES OF ATTACK
    RAO, DM
    SHARMA, G
    JOURNAL OF AIRCRAFT, 1994, 31 (04): : 915 - 921
  • [9] Fluttering flags: An experimental study of fluid forces
    Virot, Emmanuel
    Amandolese, Xavier
    Hemon, Pascal
    JOURNAL OF FLUIDS AND STRUCTURES, 2013, 43 : 385 - 401
  • [10] An experimental study of mass transfer from fluttering flags
    Nosoko, T
    Nagata, T
    Gima, S
    Irabu, K
    INTERNATIONAL COMMUNICATIONS IN HEAT AND MASS TRANSFER, 2003, 30 (02) : 185 - 196