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格栅翼减阻特性研究 被引量:15

An experimental investigation of grid fin drag reduction techniques
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摘要 为了探索减少格栅翼阻力的方法和途径 ,进行了超声速M∞ =2 .5 2 1下格栅翼的边框几何形状和尺寸以及格栅翼茎厚度、格栅几何形状对格栅翼阻力特性影响的风洞实验。结果显示 ,格栅翼的边框对格栅翼的阻力影响最大 。 An investigation of the experiments of wind tunnel for grid fins is conducted by choosing different frame cross section shape and thickness and web thickness of grid fin at supersonic speed M ∞=2.521,in order to research the characteristic of grid fin drag reduction. The results show that the frame of grid fin has the greatest effect on the grid fin drag characteristics,the grid fin drag may be reduced effectually by selecting appropriate frame cross section shape and thickness of grid fin.
出处 《流体力学实验与测量》 CSCD 北大核心 2001年第4期7-11,共5页 Experiments and Measurements in Fluid Mechanics
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参考文献6

  • 1[1]WILLIAM D W. Grid fins-a new concept for missile stability and control. AIAA-93-0035, 1993:1~11.
  • 2[2]MARK S M. An experimental investigation of grid fin drag reduction techniques.AIAA-94-1914-CP,1994:800~808.
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  • 6陈少松,徐琴,王福华,赵润祥.格栅翼组合体的超音速气动特性研究[J].弹道学报,2000,12(2):50-54. 被引量:6

二级参考文献3

  • 11,Washington W D, Miller M S. Grid fins——a new concept for missile st ability and control. AIAA-93-0035, 1993
  • 22,Miller M S, Washington W D. An experimental investigation of grid fin drag reduction techniques. AIAA-94-1914-CP, 1994
  • 33,Brooks R A. Experimental and analysis of grid fin configuration. AI AA-88-0280,1988

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