某层流验证机中央翼段失速分离特性优化及分析

doi:10.7527/S1000-6893.2022.26765

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某层流验证机中央翼段失速分离特性优化及分析

唐松祥, 李杰, 张恒, 牛笑天

西北工业大学航空学院, 西安 710072

收稿日期:2021-12-07 修回日期:2022-02-25 出版日期:2022-11-15 发布日期:2022-03-30
通讯作者: 李杰,E-mail:lijieruihao@nwpu.edu.cn E-mail:lijieruihao@nwpu.edu.cn
基金资助:
国家自然科学基金（11972304）

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

TANG Songxiang, LI Jie, ZHANG Heng, NIU Xiaotian

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

Received:2021-12-07 Revised:2022-02-25 Online:2022-11-15 Published:2022-03-30
Supported by:
National Natural Science Foundation of China (11972304)

摘要/Abstract

摘要： 针对某特殊布局形式的层流验证机中央翼段的失速分离特性，基于雷诺平均（RANS）方法分析和优化某特殊布局形式的层流验证机中央翼段失速分离特性。首先，分别采用两方程k-ω剪切应力运输（SST）湍流模型和γ-Re_θ转捩模型针对Aerospatiale-A翼型的绕流流场进行数值模拟，以验证数值方法及网格拓扑在低速计算条件下的准确性。其次，针对层流验证机中央翼段构型，以某传统翼型进行试验与数值计算，进一步说明高速条件下中央翼段构型数值模拟的准确性。最后，针对层流验证机中央翼段的翼型失速分离问题对翼型进行了优化修形，改进后的翼型有效地抑制了低速情况下前缘分离泡的发展，并将前缘分离从8°迎角延缓到12°迎角，且该优化翼型有效地保持了高速巡航状态下翼面的压力系数，对层流验证机的气动性能参数具有较好的提升。

关键词: 层流验证机, 转捩预测, 层流特性, 失速分离, 翼型优化

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

中图分类号:

V211
V224

唐松祥, 李杰, 张恒, 牛笑天. 某层流验证机中央翼段失速分离特性优化及分析[J]. 航空学报, 2022, 43(11): 526765-526765.

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.

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某层流验证机中央翼段失速分离特性优化及分析

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

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