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ACTA AERONAUTICAET ASTRONAUTICA SINICA ›› 2018, Vol. 39 ›› Issue (6): 121737-121737.doi: 10.7527/S1000-6893.2018.21737

• Fluid Mechanics and Flight Mechanics • Previous Articles     Next Articles

Design and analysis of hypersonic vehicle airfoil/wing at wide-range Mach numbers

SUN Xiangcheng, HAN Zhonghua, LIU Fei, SONG Ke, SONG Wenping   

  1. National Key Laboratory of Science and Technology on Aerodynamic Design and Research, School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China
  • Received:2017-09-11 Revised:2018-01-24 Online:2018-06-15 Published:2018-01-24
  • Supported by:
    National Natural Science Foundation of China (11272265); Aeronautical Science Foundation of China (2016ZA53011)

Abstract: The study of wider-range Mach number configuration is of great importance for the development of hypersonic vehicles. This study is aimed at designing a wider-range Mach number airfoil based on Reynolds-Averaged Navier-Stokes (RANS) equations and the surrogate-based optimization method based on kriging model. An airfoil with a lower surface of double "S" shape is designed. The aerodynamic characteristics of the designed airfoil are compared with quadrilateral and hexagon airfoils. Results show that the lift-to-drag ratio of the new airfoil is as large as 78.9 in transonic flow, and the lift-drag ratio reaches 5.94 in hypersonic flow. The aerodynamic characteristics of SANGER wing with the new airfoil is compared with that of the wing with quadrilateral and hexagon airfoils. In a word, the new airfoil as well as the wing with the new airfoil can achieve good overall aerodynamic performance at a wider-range Mach numbers, and is supposed to be applied to the design of the wider-range Mach number airfoil/wing for hypersonic vehicle applications.

Key words: airfoil design, aerodynamic optimization design, hypersonic vehicle, computational fluid dynamics, wide-range Mach numbers

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