某层流机翼验证机跨声速层流特性敏感性分析

doi:10.7527/S1000-6893.2021.26771

Abstract

Abstract: In this paper, the Reynold-Averaged Navier-Stokes (RANS) method is combined with the γ-Re_θ transition model based on local variables to investigate the transonic laminar flow characteristics and parameter sensitivity of a specially designed aircraft with laminar wing section. The RANS-based transition prediction method is validated and analyzed by the transition prediction of the DLR F-5 three-dimensional wing. The simulation results of the laminar wing section of the aircraft are compared with the corresponding experimental data, with the pressure distribution and transition location on the upper surface both showing good agreement with each other; thus proving the applicability of the calculation method proposed in this paper. This article mainly focuses on the aerodynamic characteristics of the whole aircraft in the cruise state, and the transition location and the length of the laminar flow zone on the upper surface of the middle laminar wing section under different flight conditions. According to the calculation results, the influence of laminar flow on the lift, drag and moment of the whole aircraft are further analyzed. The influence of key flow parameters such as Mach number, Reynolds number, freestream turbulence intensity and angle of attack on the transition position of the wing section surface are summarized. The results demonstrate that the transition position on the surface of the middle laminar wing section is impacted significantly by the Mach number, Reynolds number, turbulence intensity and angle of attack of the free stream. The increase of the Mach number will cause a great change in the pressure distribution, and make the transition position move forward and backward. The increase of the Reynolds number by the same amplitude will make the transition position move forward regularly. The increase in the turbulence intensity and angle of attack of the freestream will directly lead to the occurrence of an early transition, and the length of the laminar flow zone will be significantly reduced gradually.

Key words: natural laminar flow, laminar wing section, transonic laminar flow characteristic, sensitivity of laminar flow, γ-Re_θ transition model

CLC Number:

V211
V224

NIU Xiaotian, LI Jie, ZHOU Zhipeng, YANG Zhao, CHANG Mochen. Sensitivity analysis of transonic laminar flow characteristics of an aircraft with laminar wing section[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(11): 526771-526771.

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Sensitivity analysis of transonic laminar flow characteristics of an aircraft with laminar wing section

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