Multi-objective aerodynamic optimization of flying-wing configuration based on adjoint method

基于伴随方法的飞翼布局多目标气动优化设计

¹ Shenyang Aircraft Design and Research Institute, Shenyang 110035, China
² School of Aeronautics, Northwestern Polytechnic University, Xi’an 710072, China

Received: 6 November 2020

Abstract

In order to solve the multi-objective multi-constraint design in aerodynamic design of flying wing, the aerodynamic optimization design based on the adjoint method is studied. In terms of the principle of the adjoint equation, the boundary conditions and the gradient equations are derived. The Navier-Stokes equations and adjoint aerodynamic optimization design method are adopted, the optimization design of the transonic drag reduction for the two different aspect ratio of the flying wing configurations is carried out. The results of the optimization design are as follows: Under the condition of satisfying the aerodynamic and geometric constraints, the transonic shock resistance of the flying wing is weakened to a great extent, which proves that the developed method has high optimization efficiency and good optimization effect in the multi-objective multi-constraint aerodynamic design of the flying wing.

摘要

针对飞翼布局气动设计中的多目标多约束设计问题，开展了基于伴随方法的气动优化设计研究。构建合理的统一目标函数，并根据伴随方法基本原理推导了相应的伴随方程边界条件及梯度求解方程，采用N-S方程和伴随气动优化设计方法，进行了2种不同展弦比飞翼布局的跨声速减阻优化设计，优化结果表明：在满足气动、几何约束的前提下，飞翼布局跨声速激波阻力被很大程度削弱，证明了所发展的方法在飞翼布局多目标多约束气动设计上具有较高的优化效率和良好的优化效果。