Research progress and engineering application of flow control technology for drag and heat reduction of high-speed vehicles

被引：0
作者：
Zhu G. [1 ]
Yao S. [1 ,2 ]
Duan Y. [1 ,2 ]
机构：
[1] China Academy of Launch Vehicle Technology, Beijing
[2] Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 15期
基金：
中国国家自然科学基金;
关键词：
boundary layer; drag reduction; flow control; heat reduction; shock wave;
D O I：
10.7527/S1000-6893.2023.29049
中图分类号：
学科分类号：
摘要：
Drag and heat reductions are two core issues in the design of high-speed flight vehicles. Drag reduction can enhance the lift-drag ratio of vehicles and decrease the fuel consumption，while heat reduction can reduce the weight of thermal protection system and promote the effective load of flight vehicles. Drag and heat reductions are the key technologies to improve the fine design and enhance the flight performance. This paper mainly reviews the research status of flow control technology for drag and heat reductions of shock wave and boundary layer，from the perspective of the engineering requirements for drag and heat reductions of high-speed flight vehicles. This paper also points out the existing problems in engineering application and the direction that should be paid close attention to in the future，to realize the engineering application of active flow control of flight vehicles and improve the flight performance. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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  • [11] BURBANK P B, STALLINGS R L., Heat-transfer and pressure measurements on a flat-face cylinder at a mach number range of 2.49 to 4.44：NASA TM X-19［R］, (1959)
  • [12] ZHANG J，, XIAO F，, HUANG W，, Et al., A survey of drag and heat reduction induced by forward-facing cavity and its combinations［J］, Aero Weaponry, 28, 4, pp. 16-23, (2021)
  • [13] YADAV R, GUVEN U., Aerothermodynamics of a hypersonic vehicle with a forward-facing parabolic cavity at nose［J］, Proceedings of the Institution of Mechanical Engineers， Part G： Journal of Aerospace Engineering, 228, 10, pp. 1863-1874, (2014)
  • [14] YADAV R, GUVEN U., Aerodynamic heating of a hypersonic projectile with forward-facing ellipsoid cavity at nose［J］, Journal of Spacecraft and Rockets, 52, 1, pp. 157-165, (2015)
  • [15] Heat fluxes inside a cavity placed at the nose of a projectile measured in a shock tunnel at Mach 4.5［C］, New Results in Numerical and Experimental Fluid Mechanics VI, pp. 309-316, (2007)
  • [16] SILTON S I, GOLDSTEIN D B., Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow ［J］, Journal of Fluid Mechanics, 528, pp. 297-321, (2005)
  • [17] LU H B, LIU W Q., Investigation on thermal protection efficiency of hypersonic vehicle nose with forward-facing cavity［J］, Journal of Astronautics, 33, 8, pp. 1013-1018, (2012)
  • [18] LOPATOFF M., Wind-flow study of pressure-drag reduction at transonic speed by projecting a jet of air from the nose of a prolate spheroid of fineness ratio 6：NACA-RM-L51E09［R］, (1951)
  • [19] WARREN C H E., An experimental investigation of the effect of ejecting a coolant gas at the nose of a bluff body ［J］, Journal of Fluid Mechanics, 8, 3, (1960)
  • [20] TANI Y., Enhancement of aerodynamic heating reduction in high enthalpy flows with opposing jet［C］, Proceedings of the 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, (2011)
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