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前体边条控制技术应用 被引量:3

Application of Forebody Strake Control Technology
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摘要 采用各种不同形状和安装位置的前体边条对前体涡进行控制,研究各种前体边条对全机大迎角气动特性的影响。 In the present paper a series of forebody strakes were applied in order to control the forebody vortex, and the effects of forebody strake on the aerodynamical characteristics at high angles of attack were studied.
出处 《空气动力学学报》 EI CSCD 北大核心 1997年第1期54-58,共5页 Acta Aerodynamica Sinica
关键词 前体涡控制 前体边条 大迎角 机翼空气动力学 forebody vortex controlling forebody strake aerodynamical characteristics at high angles of attack
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同被引文献28

  • 1周伟江,李锋,汪翼云.三角翼跨声速动态失速与涡破裂特性研究[J].航空学报,1996,17(6):671-677. 被引量:5
  • 2邓学蓥.细长旋成体大迎角流场结构与分区特性研究[A]..第一届全国低跨超声速空气动力学会议大会邀请报告[C].,2001年10月..
  • 3COOPER M, GAPCYNSKI J. P. and HASEL L. E. A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees [R]. NACA RM-L52G14a, October 30, 1952.
  • 4BERNHARDT J. E and WILLIAMS D.B. Close-Loop control of forebody flow asymmetry [J]. Journal of Aircraft, 2000,37(3):491-498.
  • 5MOSKOVITZ C. A, HALL R. M, and DEJARNETTE F.R.New device or controlling asymmetric flowfields on forebody at large alpha [J]. Journal of Aircraft, 1991,28(7):456-462.
  • 6LAMONT P. J. Pressure around an inclined ogive cylinder with laminar transitional or turbulent separation [J]. AIKA J, 1982,20(11).
  • 7SKOW A M, ERICKSON G E. Modern fighter aircraft design for high angle of attack maneuvering: AGARD I,S- 121[R]. Paris: AGARD. 1982.
  • 8POLHAMUS E C. Prediction of vortex lift characteristics by a leading-edge suction analogy[J]. Journal of Aircraft,1971, 8(4) 193-199.
  • 9DONOHOE S R, gANNINK W 3, Su{aee reflective visu- alisations of shock-wave/vortex interactions above a delta wing[J]. AIAA Journal, 1997, 35(10): 1568-1573.
  • 10EKATERINARIS J A, SCHIFF L B. Vortical flows over delta wings and numerical prediction of vortex breakdown: AIAA-1990 0102[R]. Reston: AIAA, 1990.

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