飞机大攻角气动力建模研究进展

ADVANCES IN AERODYNAMIC MODELING OF AIRPLANE AT HIGH ANGLES OF ATTACK

在飞机大攻角气动力建模领域中，将已有的模型归纳为代数模型、积分模型和微分方程模型三类。文章给出了非线性气动力两种常用的代数模型──多项大模型和样条函数模型；简要阐述了非定常气动力积分模型的建立及其简化过程；重点综述了新近开发的微分方程模型，从有分离的翼型和有涡破裂的三角翼气动力模型形式推广出微分形式的飞机大攻角气动力模型。应用实例表明，积分模型和微分方程模型能够描述大攻角气动力的非定常增升和迟滞效应。

The main advances in aerodynamic modeling of airplane at high angles of attack are systematically reviewcd.The existing models are divided into three kinds: algebraical, integral, and of differential equations. Two of algebraical models, polynomial and spline function,which have been adopted extensively, are introduced. The process of unsteady aerodynamic modeling by integral and the simplification of the model are briefly described.The differential equation model, developed recently, is emphatically reviewed. The aerodynamic model of airplane at high angles of attack in the form of differential equation is obtained by extending the models of airfoils with flow separation and delta wingswith vortex breakdown.The application examples show that the integralmodel and the differential equation model can describe aerodynamic effects of unsteady high lift and hysteresis at high angles of attack.