Stall separation optimization and analysis of middle wing section on specially configured laminar flight

TANG Songxiang; LI Jie; ZHANG Heng; NIU Xiaotian

doi:10.7527/S1000-6893.2022.26765

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2022 , Vol. 43 >Issue 11: 526765 - 526765

DOI: https://doi.org/10.7527/S1000-6893.2022.26765

Articles

Stall separation optimization and analysis of middle wing section on specially configured laminar flight

TANG Songxiang ,
LI Jie ,
ZHANG Heng ,
NIU Xiaotian

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School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received date: 2021-12-07

Revised date: 2022-02-25

Online published: 2022-03-30

Supported by

National Natural Science Foundation of China (11972304)

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Abstract

The stall separation of the middle wing section on a specially configured laminar flight, the airfoil of the middle wing section was analyzed and optimized based on the Reynolds-Averaged Navier-Stokes (RANS) method. The standard k-ω Shear Stress Transport (SST) turbulence model and the γ-Re_θ transition model were adopted to calculate the flow field of an Aerospatiale A-airfoil to verify the accuracy of both the numerical method and the grid topology at low speed. To verify the model accuracy of the laminar middle wing section configuration at high speed, the flow field of a traditional airfoil was calculated, and the result compared with those of the wind tunnel test under the same condition. Finally, the airfoil profile was optimized for the stall separation of the laminar middle wing section. The result showed that the modified airfoil could retard the development of the separation bubble at the leading edge, and the starting of separation was delayed from the angle of attack 8° to 12°. Furthermore, the modified wing section effectively maintained the distribution of the pressure coefficient under the high speed cruising condition with a better aerodynamic characteristic compared with the original one.

Key words： specially configured laminar flight; transition prediction; laminar characteristics; stall separation; airfoil optimization

Cite this article

TANG Songxiang , LI Jie , ZHANG Heng , NIU Xiaotian . Stall separation optimization and analysis of middle wing section on specially configured laminar flight[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022 , 43(11) : 526765 -526765 . DOI: 10.7527/S1000-6893.2022.26765

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