Volume 31 Issue 6
Jun.  2016
Turn off MathJax
Article Contents
NIE Shuai, CAO Yi-hua, TIAN Si-ying. Effect on parafoil aerodynamic performance of leading edge[J]. Journal of Aerospace Power, 2016, 31(6): 1477-1485. doi: 10.13224/j.cnki.jasp.2016.06.025
Citation: NIE Shuai, CAO Yi-hua, TIAN Si-ying. Effect on parafoil aerodynamic performance of leading edge[J]. Journal of Aerospace Power, 2016, 31(6): 1477-1485. doi: 10.13224/j.cnki.jasp.2016.06.025

Effect on parafoil aerodynamic performance of leading edge

doi: 10.13224/j.cnki.jasp.2016.06.025
  • Received Date: 2014-06-10
  • Publish Date: 2016-06-28
  • Two-dimensional and three-dimensional steady flow field of parafoils with profile based on Clark-Y and with different leading edges and arc-anhedral angles were numerically simulated without considering the impact of flexibility, so as to study the effect of leading edge and arc-anhedral angle on parafoil aerodynamic performance. Results show that while enhancing the glide performance, the leading edge cut leads to the decrease of lift coefficient and increase of drag coefficient, and the reduction of lift coefficient gets more severe with the increase of cut size; the lip located in leading edge cut can effectively reduces the profile drag of parafoil; the lift reduction of parafoil increases as the value of arc-anhedral angle gets larger; in addition, this modified LLT (lift line theory) model exhibits high accuracy within the range of small and median angles of attack.

     

  • loading
  • [1]
    Knacke T W.Parachute recover systems design manual[R].Santa Barbara,California:Para Publishing,1991.
    [2]
    Nicolaides J D.Parafoil wind tunnel tests [R].South Bend,Indiana:University of Notre Dame,1971.
    [3]
    Lingard J S.Precision aerial delivery seminar ram-air parachute design[C]//13th AIAA Aerodynamic Decelerator Systems Technology Conference.Clearwater:American Institute of Aeronautics and Astronautics,1995:1-51.
    [4]
    Lingard J S,The aerodynamic of gliding parachute[R].Royal Aeronautical Society,RAS A88-11201,1986.
    [5]
    Ross J C.Computation aerodynamics in the design and analysis of ram-air-inflated wings[R].AIAA 93-1228,1993.
    [6]
    Balaji R,Mittal S,Rai A K.Effect of leadingedge cut on the aerodynamics of ram-air parachutes [J]. International Journal for Numerical Methods in Fluids,2005,47(1):1-17.
    [7]
    Mohammadi M A,Johari H.Computation of flow over a high-performance parafoil canopy[J].Journal of Aircraft,2010,47(4):1338-1345.
    [8]
    Eslambolchi A,Johari H,Simulation of flowfield around a ram-air personnel parachute canopy[C]//22nd AIAA Aerodynamic Decelerator Systems Technology Conference.Daytona:American Institute of Aeronautics and Astronautics,2013:1628-1636.
    [9]
    李扬,夏刚,秦子增.基于预处理方法的冲压式翼伞非定常气动特性 数值研究[J].航天返回与遥感,2004,25(2):1-4. LI Yang,XIA Gang,QING Zizeng.Proconditioning numerical simulation of unsteady aerodynamics of ram-air parachutes[J].Spacecraft Recovery & Remote Sensing,2004,25(2):1-4.(in Chinese)
    [10]
    李健.前缘切口对冲压式翼伞的气动力影响[J].航天返回与遥感,2005,26(1):36-41. LI Jian.The aerodynamic influence of the cutter of the front edge of parafoil[J].Spacecraft Recovery & Remote Sensing,2005,26(1):36-41.(in Chinese)
    [11]
    Han Y H,Yang C X,Wang Y W,et al.Aerodynamics simulation of a large multi-cells parafoil[R].AIAA-2009-2978,2009.
    [12]
    朱旭,曹义华.翼伞平面形状对翼伞气动性能的影响[J].航空学报,2011,32(11):1988-2007. ZHU Xu,CAO Yihua.Numerical simulation of platform geometry effect on parafoil aerodynamic performance[J].Acta Aeronautica et Astronautica Sinica,2011,32(11):1988-2007.(in Chinese)
    [13]
    朱旭,曹义华.翼伞弧面下反角、翼型和前缘切口对翼伞气动性能的影响[J].航空学报,2012,33(6):1189-1200. ZHU Xu,CAO Yihua.Effects of Arc-anhedral Angle,Airfoil and Leading Edge Cut on Parafoil Aerodynamic Performance[J].Acta Aeronautica et Astronautica Sinica,2012,33(6):1189-1200.(in Chinese)
    [14]
    Silverstein A.Scaleeffect on Clark-Y airfoil characteristics from NASA full-scale wind-tunnel tests[R].NASA-TR-502,1935.
    [15]
    Ware G M,Hassell J L.Wind-tunnel investigation of ram-air inflated all flexible wings of aspect ratio 1.0 to 3.0[R].NASA-TM-SX-1923,1969.
    [16]
    Slegers N,Costello M.Aspects of control for a parafoil and payload system[J].Journal of Guidance,Control,and Dynamics.2003,26(6):898-905.
    [17]
    Gonzalez M A.Prandtl theory applied to paraglider aerodynamics[R].AIAA 93-1220,1993.
    [18]
    Melin T.A vortex lattice MATLAB implementation for linear aerodynamic wing applications for linear aerodynamic wing applications[D].Sweden,Stockholm:Royal Institute of Technology,2000.
  • 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 (1017) PDF downloads(596) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return