典型三角翼的大迎角动态流场分析

飞行器大迎角动态机动飞行时,流场会产生流动分离和涡破碎,气动力表现出很强的非线性和非定常特征,需要对大迎角特性作出进一步研究。该文以CFD技术为基础,通过对典型三角翼模型大迎角俯仰振荡过程中气动力和流场的深入分析,展现模型大迎角动态流场发生流动分离和涡破碎的全过程,揭示大迎角下非线性气动力变化的物理机理。

During dynamic maneuvering flight at high angles of attack,flow separation and vortex fragmentation occur in the flow field,and aerodynamic forces exhibit strong nonlinear and unsteady characteristics.Further research is needed on the characteristics of high angles of attack.This article is based on CFD technology,and through in-depth analysis of the aerodynamic and flow fields during the high angle of attack pitch oscillation process of a typical delta wing model,it presents the entire process of flow separation and vortex fragmentation in the dynamic flow field of the model at high angles of attack,revealing the physical mechanism of nonlinear aerodynamic changes at high angles of attack.