基于Euler方程的直升机旋翼翼型反设计方法

An Inverse Design Method for the Helicopter Rotor Airfoil Based on Euler Equation

直升机旋翼流场的求解和贴体网格的生成是进行旋翼翼型反设计的关键,本文采用Euler方程求解直升机旋翼翼型流场,并通过求解泊松方程生成围绕翼型的网格。在此基础上,结合线化二维亚音速和超音速流的小扰动理论,采用MGM方程作为反设计方程,基于有限差分方法建立一套直升机旋翼翼型反设计的迭代方法。在给定的目标压力分布条件下,与CFD方法相结合,反设计得出满足要求的翼型,并与目标翼型吻合良好,表明本文建立的翼型反设计方法能够有效地用于直升机旋翼翼型设计。

The solution of rotor flowfield and the generation of the body-conforming grids are the key of the inverse design investigation for helicopter rotor airfoil.The flowfield of helicopter rotor is solved by using Euler equations,and the grids around the rotor airfoil are generated by employing Poisson equations approach.Then an inverse iteration approach based on the finite difference method is developed by combining the two dimensional linear subsonic and supersonic small disturbance equations and the present airfoil inverse equation is using the MGM equation.The new airfoil can be designed through combining the CFD method with the inverse iteration method according the target pressure distribution.The calculated results indicate that the present inverse method can be used to design the airfoil for helicopter rotor effectively.