YANG Li-zhi, GAO Zheng-hong. Computation of Field Structure and Aerodynamic Characteristics of Delta Wings at High Angles of Attack[J]. Applied Mathematics and Mechanics, 2005, 26(6): 734-742.
Citation: YANG Li-zhi, GAO Zheng-hong. Computation of Field Structure and Aerodynamic Characteristics of Delta Wings at High Angles of Attack[J]. Applied Mathematics and Mechanics, 2005, 26(6): 734-742.

Computation of Field Structure and Aerodynamic Characteristics of Delta Wings at High Angles of Attack

  • Received Date: 2003-03-02
  • Rev Recd Date: 2005-03-12
  • Publish Date: 2005-06-15
  • A numerical investigation of the structure of the vortical flowfield over delta wings at high angles of attack in longitudinal and with small sideslip angle is presented.Three-dimensional Navier-Stokes numerical simulations were carried out to predict the complex leeward-side flowfield characteristics that are dominated by the effect of the breakdown of the leading-edge vortices.The methods that analyze the flowfield structure quantitatively were given by using flowfield data from the computational results.In the region before the vortex breakdown,the vortex axes are approximated as being straight line.As the angle of attack increases,the vortex axes are closer to the root chord,and farther away from the wing surface.Along the vortex axes,as the adverse pressure gradients occur,the axial velocity decreases,that is lambda is negative,so the vortex is unstable,and it is possible to breakdown.The occurrence of the breakdown results in the instability of lateral motion for a delta wing,and the lateral moment diverges after a small perturbation occurs at high angles of attack.However,after a critical angle of attack is reached,the vortices breakdown completely at the wing apex,and the instability resulting from the vortex breakdown disappears.
  • loading
  • [1]
    高正红.关于绕任意机翼非定常流动的一种无条件稳定的欧拉方程解[J].应用数学和力学,1995,16(12):1123—1134.
    [2]
    Jameson A,Schmidt W,Turkel E.Numerical solutions of the Euler equations by finite volume methods using Runge-Kutta time stepping scheme[R]. AIAA Paper 81-1259, 1981.
    [3]
    刘谋佶,吕志咏,丘成昊,等.边条翼与旋涡分离流[M].北京: 北京航空学院出版社, 1988.
    [4]
    Fujii K,Schiff L B. Numerical simulation of vortical flows over a strake-delta wing[J].AIAA J,1989,27(9):1153—1162. doi: 10.2514/3.10239
    [5]
    Agrawal S,Barnett R M,Robinson B A. Numerical investigation of vortex breakdown on a delta wing[J].AIAA J,1992,30(3):584—591. doi: 10.2514/3.10960
    [6]
    张涵信.旋涡沿轴线的非线性分叉[J].空气动力学学报,1994,12(3):243—250.
    [7]
    Soltani M R,Bragg M B. Early vortex breakdown on a delta wing in pitch [J].AIAA J,1993,31(12):2283—2249. doi: 10.2514/3.11926
    [8]
    Morton S A,Forsythe J R.Analysis of delta wing vortical substructures using detached-eddy simulation[R]. AIAA Paper,2002-2968,2002.
    [9]
    林炳秋.细长三角翼前缘分离涡破裂特性计算方法[J].空气动力学学报,1985,3(3):63—71.
    [10]
    Abdelhamid Yahia A,Kandil Osama A.Effect of reduced frequency on super maneuver delta wing[R]. AIAA Paper 98-0415,1998.
    [11]
    Rusak Z,Lamb D. Prediction of vortex breakdown in leading edge vortices above slender delta wings[R]. AIAA Paper 98-2860, 1998.
  • 加载中

Catalog

    通讯作者: 陈斌, bchen63@163.com
    • 1. 

      沈阳化工大学材料科学与工程学院 沈阳 110142

    1. 本站搜索
    2. 百度学术搜索
    3. 万方数据库搜索
    4. CNKI搜索

    Article Metrics

    Article views (2405) PDF downloads(824) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return