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Drag Reduction for Spike Attached to Blunt-Nosed Body at Mach 6

机译:减少减震力,以使附着在马赫数为6的钝头物体上的尖刺

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摘要

A high-speed flow over a blunt body generates a bow shock wave in front of it, which causes a rather high surface pressurernand, as a result, high aerodynamic drag. The surface pressure on the blunt body can be substantially reduced if a conical shock wave is generated by attaching a forward-facing spike. Thus, the introduction of the spike decreases the drag and increases the lift coefficient. The spike produces a region of recirculating separated flow that shields the blunt-nosed body from the incoming flow. The applicability of the spike is limited due to the possible appearance of flow oscillations in the separation region, which may reduce its positive effects and may cause aerodynamic disturbances during the flight [1].
机译:钝体上的高速流动会在其前面产生弓形冲击波,这会产生相当高的表面压力,从而导致高气动阻力。如果通过安装朝前的尖头产生圆锥形的冲击波,则可以大大降低钝体上的表面压力。因此,尖峰的引入减小了阻力并增加了升力系数。尖峰产生一个再循环的分离流区域,该区域将钝头体与进入的流隔离开。尖峰的适用性受到限制,因为在分离区域中可能会出现流动振荡,这可能会降低其积极影响,并可能在飞行过程中引起气动干扰[1]。

著录项

  • 来源
    《Journal of Spacecraft and Rockets》 |2010年第1期|219-222|共4页
  • 作者单位

    Vikram Sharabhai Space Center, Trivandrum 695 022, India;

    rnNanyang Technological University,Singapore 639 798, Republic of Singapore;

    rnIndian Institute of Technology, Kanpur 208 016, India;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
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