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首页> 外文期刊>Aerospace science and technology >Drag reduction investigation for hypersonic lifting-body vehicles with aerospike and long penetration mode counterflowing jet
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Drag reduction investigation for hypersonic lifting-body vehicles with aerospike and long penetration mode counterflowing jet

机译：具有气溶胶和长穿透模式逆流射流的高超音速起重汽车的减阻研究

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摘要

This study describes numerical computations of aerospike and counterflowing jet as the drag reduction approach of a hypersonic lifting-body model for Mach 8 flow at 40 km altitude. The three-dimensional Reynolds-average Navier-Stokes equations and the laminar condition have been utilized to obtain the flow field properties. Both steady-state and time-accurate computations are performed for the models in order to investigate the drag reduction effect and the periodic oscillation characteristics of long penetration mode (LPM) jet. The obtained results show that both methods can significantly modify the external flowfields and strongly weaken or disperse the shock-waves of the vehicle, then achieve an obvious drag reduction effect in the range of small angles of attack. This value is 7.25% for the model with aerospike and 8.80% for the model with counterflowing jet at angle of attack of 6 degrees. Compared with the aerospike, the counterflowing jet shows a better drag reduction effect in the gliding angle of attack, and this leads to a larger lift-to-drag ratio of 3.58. Meanwhile, the displacement of center of pressure of the whole vehicle is smaller in the flight phase. The oscillation frequency of the counterflowing jet at angle of attack of 6 is 444 Hz, and the oscillation characteristics of the drag force is due to the variation of the pressure distribution induced by the oscillation of the shock wave structure. The results may be of high practical significance and show the possibility of developing a feasible system using the counterflowing jet as an active flow control to reduce the drag force during the gliding phase with maximum lift-to-drag ratio. (C) 2018 Published by Elsevier Masson SAS.
机译：这项研究将气溶胶和逆流射流的数值计算描述为高超声速提升机体模型在40 km高度下的高超声速提升体模型的减阻方法。利用三维雷诺平均Navier-Stokes方程和层流条件来获得流场特性。为了研究减阻效果和长穿透模式（LPM）射流的周期性振荡特性，对模型进行了稳态和时间精确计算。所得结果表明，两种方法都可以显着改变外部流场，大大减弱或分散车辆的冲击波，在较小的迎角范围内达到明显的减阻效果。对于具有气钉的模型，该值是7.25％，对于具有6度迎角的逆流射流的模型，该值是8.80％。与气动尖峰相比，逆流射流在滑翔迎角上显示出更好的减阻效果，这导致更大的升阻比3.58。同时，在飞行阶段，整个车辆的压力中心的位移较小。逆流射流​​在迎角为6时的振荡频率为444 Hz，并且拖曳力的振荡特性是由于冲击波结构的振荡引起的压力分布变化而引起的。结果可能具有很高的实际意义，并显示了开发一种可行的系统的可能性，该系统使用逆流射流作为主动流量控制装置，以减小滑行阶段的阻力，并具有最大的升阻比。 （C）2018年由Elsevier Masson SAS发布。

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  • 来源
    《Aerospace science and technology》 |2018年第5期|361-373|共13页
  • 作者

    Deng Fan; Xie Feng; Qin Ning; Huang Wei; Wang Lansong; Chu Hongyu;

  • 作者单位

    OneSpace Sci & Technol CO Ltd, Gen Control Dept, Beijing 100080, 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;

    Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China;

    China Acad Launch Vehicle Technol, Beijing 100076, Peoples R China;

    China Acad Launch Vehicle Technol, Beijing 100076, Peoples R China;

  • 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
  • 中图分类
  • 关键词

    Hypersonic; Lifting-body vehicle; Drag reduction; Aerospike; Counterflowing jet;

    机译：高超音速;起重车辆;减阻;气溶胶;逆流喷射;

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