Adjoint-based robust optimization design of laminar flow wing under flight condition uncertainties

作     者：Yifu CHEN Hanyue RAO Yiju DENG Tihao YANG Yayun SHI Junqiang BAI Yifu CHEN;Hanyue RAO;Yiju DENG;Tihao YANG;Yayun SHI;Junqiang BAI

作者机构：School of AeronauticsNorthwestern Polytechnical UniversityXi’an 710072China The First Aircraft Design and Research InstituteXi’an 710089China State Key Laboratory for Strength and Vibration of Mechanical StructuresSchool of Aerospace EngineeringXi’an Jiaotong UniversityXi’an 710049China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2023年第36卷第6期

页      面：19-34页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 0801[工学-力学（可授工学、理学学位）] 

基　　金：We are grateful for the excellent framework built by the research team of Prof. Martins in the University of Michigan. All the extended work in this paper is supported by the well-developed open-source optimization framework MACH-Aero. The framework contains the CFD and adjoint solver ADflow (https://github.com/mdolab/adflow)  the geometry parameterization module pyGeo 46 using Free Form Deformation (https://github.com/mdolab/pygeo)  Volume mesh warping module Idwarp 47 using an inverse distance method (https://github.com/mdolab/idwarp)  an optimizer wrapper pyOptSparse 48 for formulating and solving nonlinear constrained optimization problem (https://github.com/mdolab/pyoptsparse). The SNOPT algorithm 49 in pyOptSparse was used for this work 

主　　题：Adjoint method Gradient-based optimization Laminar-turbulent transition Robust design Uncertainty propagation 

摘      要：It is an inherent uncertainty problem that the application of laminar flow technology to the wing of large passenger aircraft is affected by flight *** order to seek a more robust natural laminar flow control effect,it is necessary to develop an effective optimization design ***,attention must be given to the impact of crossflow(CF)instability brought on by the sweep *** paper constructs a robust optimization design framework based on discrete adjoint methods and non-intrusive polynomial *** prediction is implemented by coupled Reynolds-Averaged Navier-Stokes(RANS)and simplified e^(N)method,which can consider both Tollmien-Schlichting(TS)wave and crossflow vortex *** have performed gradient enhancement processing on the general Polynomial Chaos Expansion(PCE),which is advantageous to reduce the computational cost of single uncertainty *** processing takes advantage of the gradient information obtained by solving the coupled adjoint equations considering *** statistical moment gradient solution used for the robust optimization design also uses the derivatives of coupled adjoint *** framework is applied to the robust design of a 25°swept wing with infinite span in transonic *** uncertainty quantification and sensitivity analysis on the baseline wing shows that the uncertainty quantification method in this paper has high accuracy,and qualitatively reveals the factors that dominate in different flow field *** the robust optimization design,the mean and standard deviation of the drag coefficient can be reduced by 29%and 45%,respectively,and compared with the deterministic optimization design results,there is less possibility of forming shock waves under flight condition *** optimization results illustrate the trade-off between the transition delay and the wave drag reduction.