基于离散伴随的层流翼优化设计方法

杨体浩; 王一雯; 王雨桐; 史亚云; 周铸

doi:10.7527/S1000-6893.2021.26132

航空学报 >

2022 , Vol. 43 >Issue 12: 126132 - 126132

DOI: https://doi.org/10.7527/S1000-6893.2021.26132

流体力学与飞行力学

基于离散伴随的层流翼优化设计方法

杨体浩 ,
王一雯 ,
王雨桐 ,
史亚云 ,
周铸

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1. 西北工业大学航空学院, 西安 710072;
2. 西北工业大学无人系统技术研究院, 西安 710072;
3. 西安交通大学航天学院, 西安 710049;
4. 中国空气动力研究与发展中心, 绵阳 621000

收稿日期: 2021-07-20

修回日期: 2021-09-22

网络出版日期: 2022-01-26

基金资助

国家自然科学基金（11902320，12002284）

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Discrete adjoint-based optimization approach for laminar flow wings

YANG Tihao ,
WANG Yiwen ,
WANG Yutong ,
SHI Yayun ,
ZHOU Zhu

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1. School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China;
2. Unmanned System Research Institute, Northwestern Polytechnical University, Xi'an 710072, China;
3. School of Aerospace, Xi'an Jiaotong University, Xi'an 710049, China;
4. China Aerodynamics Research and Development Center, Mianyang 621000, China

Received date: 2021-07-20

Revised date: 2021-09-22

Online published: 2022-01-26

Supported by

National Natural Science Foundation of China (11902320, 12002284)

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摘要

层流技术是未来发展绿色航空的核心技术，可处理大规模设计变量的高效、鲁棒的优化设计方法是推动层流技术工程应用转化的关键环节之一。基于高可信度RANS求解器，结合准三维层流边界层方程、Drela-Giles和C1准则，建立了可同时捕捉Tollmien-Schlichting （TS）和Crossflow （CF）不稳定性的转捩预测方法，与典型风洞和飞行试验对比，验证了该方法的可靠性。通过严格物面插值、获得准确的间歇因子函数以剔除气动力计算引入的数值噪声，精确推导了考虑转捩的耦合伴随方程，并结合无矩阵存储技术、链式求导法则、反向混合自动微分及Coupled Krylov （CK）算法发展了耦合伴随方程高效求解方法，最终建立了基于离散伴随的层流翼梯度优化设计方法。针对典型客机翼身组合体构型的气动优化显著推迟了转捩，获得了10.48%的减阻收益。优化结果表明，建立的层流翼梯度优化方法能够有效处理多种转捩机制并存的复杂三维层流翼优化问题。

关键词： 离散伴随; 层流转捩; 减阻; 梯度优化; 流向转捩; 横流转捩

本文引用格式

杨体浩 , 王一雯 , 王雨桐 , 史亚云 , 周铸 . 基于离散伴随的层流翼优化设计方法[J]. 航空学报, 2022 , 43(12) : 126132 -126132 . DOI: 10.7527/S1000-6893.2021.26132

Abstract

Laminar flow is one of the key technologies in the future development of green aviation, while an efficient and reliable design optimization approach for problems with a large number of design variables is the key to promoting the industrial application of the laminar flow technique. Based on the high-fidelity RANS solver, and combined with the quasi-three-dimensional laminar boundary layer equation, Drela-Giles and C1 criteria, a transition prediction method, which can simultaneously capture Tollmien-Schlichting (TS) and Crossflow (CF) instabilities, is established. Comparison of the simulation results with typical wind tunnel and flight tests shows the reliability of the simulation approach. An accurate intermittency function is obtained by strictly interpolating the surface values to eliminate the numerical noise for the aerodynamic forces simulation. The coupled adjoint equation considering transition is derived accurately, and solved efficiently by combining the matrix-free technique, the chain rule, the hybrid reverse automatic differentiation, and the Coupled Krylov (CK) algorithm. Finally, the discrete adjoint-based laminar flow wings optimization method is built. The optimization of a wing-body configuration with typical characteristics of regional airliners demonstrates that the transition is effectively delayed, with 10.48% of the total drag reduced. The optimization results reveal that the gradient-based laminar flow wings optimization framework can deal with complex three-dimensional laminar flow wings optimization problems with multiple transition mechanisms.

Key words： discrete adjoint; laminar-turbulent transition; drag reduction; gradient-based optimization; streamwise transition; crossflow transition

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