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Spike Effects on Drag Reduction for Hypersonic Lifting Body

机译：尖峰对高超声速举升体减阻的影响

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摘要

A high lift-to-drag ratio is considered crucial for high-altitude and long-endurance hypersonic vehicles. One of the simplest and most useful methods is to install an aerospike in front of the vehicle's nose. In this paper, the flight aerodynamic characteristics are investigated by simulating and comparing the lifting body with or without the aerospikes at Ma=8. The flowfields around aerospikes using different spike lengths and a hemispherical disk along with the lifting body are analyzed. The results of aerodynamic characteristics indicate that L/D=2 is the best ratio of the spike length to the nose diameter. By comparing with the baseline model, the maximum drag reduction of the nose's part is 49.3% at =8deg using a hemispherical disk. In addition, three shapes of aerospike disks are compared to search for the best disk for hypersonic drag reduction. The best drag reduction is found for the double flat-faced disk aerospike, which gives a pressure drag reduction of 60.5% of the nose's part at =8deg. Furthermore, when the flight angle of attack increases, the drag increases significantly. Employing a certain installation angle is shown to effectively improve the drag reduction around the angle of attack and results in improving the lift-to-drag ratio. At the end, the lift-to-drag ratio of the final optimized design is 9.1% better than that of the baseline model. The pressure center is moved forward by 1.6%, barely influencing the vertical static stability of the vehicle.
机译：对于高海拔和长寿命的高超音速飞行器来说，高升阻比被认为是至关重要的。一种最简单，最有用的方法是在汽车的机头前安装一个气钉。本文通过模拟和比较在Ma = 8时有或没有气钉的提升体来研究飞行空气动力特性。分析了使用不同尖峰长度和半球形圆盘以及提升体的气钉周围的流场。空气动力学特性的结果表明，L / D = 2是尖峰长度与机头直径的最佳比率。通过与基线模型进行比较，使用半球形圆盘在= 8deg时，鼻子部分的最大阻力减小为49.3％。此外，还比较了三种形状的气钉盘，以寻找最佳的盘片以降低超音速阻力。对于双平面圆盘气锤，可以找到最佳的减阻效果，在= 8deg的情况下，其鼻部压力减阻值为60.5％。此外，当飞行迎角增大时，阻力显着增大。显示出采用一定的安装角度可以有效地改善迎角附近的阻力减小，并提高升阻比。最后，最终优化设计的提升/拖动比比基线模型高9.1％。压力中心向前移动1.6％，几乎不影响车辆的垂直静态稳定性。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2017年第6期|1185-1195|共11页
  • 作者

    Deng Fan; Jiao Zihan; Liang Bingbing; Xie Feng; Qin Ning;

  • 作者单位

    China Acad Launch Vehicle Technol, Sci & Technol Space Phys Lab, Aircraft Design Grp, Beijing 100076, Peoples R China|Univ Sheffield, Dept Mech Engn, Sheffield S1 3JD, S Yorkshire, England;

    China Acad Launch Vehicle Technol, Sci & Technol Space Phys Lab, Aircraft Design Grp, Beijing 100076, Peoples R China;

    China Acad Launch Vehicle Technol, Sci & Technol Space Phys Lab, Aircraft Design Grp, Beijing 100076, Peoples R China;

    Univ Sheffield, Dept Mech Engn, Sheffield S1 3JD, S Yorkshire, England;

    Univ Sheffield, Dept Mech Engn, Sheffield S1 3JD, S Yorkshire, England;

  • 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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