基于目标压力分布的旋翼先进气动外形反设计分析方法

doi:10.7527/S1000-6893.2013.0267

Abstract

Abstract:

An inverse design method for a helicopter rotor with advanced aerodynamic configuration is established based on Reynolds-averaged Navier-Stokes (RANS) equations, moving-embedded grids, target pressure distributions and the iterative residual correction principle. In order to avoid the distortion of the grids around the blade due to configuration change, a fast and automated generation method of the body-fitted and orthogonal grids around the rotor blade is employed by solving the Poisson equations. To improve the quality and robustness of the moving-embedded grids, a strategy of grid generation is proposed by combining the interpolation of section grids and the folding of blade tip grids. Simultaneously, a new approach for determining the hole boundary and searching donor cells is created by the combination of "Top Map" and "Inverse Map" methods. The solution of the unsteady flowfield of the rotor is accomplished by employing the Navier-Stokes equations and a dual-time scheme. The convective flux is calculated by a Roe-MUSCL scheme, and a preconditioning approach is employed to overcome the stiffness of flowfield convergence. Based upon the computational fluid dynamics (CFD) numerical simulation, the MGM (Modified Garabedia-McFadden) inverse design overdetermined equations are established at different azimuthal angles based on the residual of pressure coefficients, and the weight factors at different azimuthal angles are set up according to the restriction of shock wave separation and dynamic stall. An inverse design method for the aerodynamic configuration (airfoil) of the rotor is developed by the least square solution of the overdetermined MGM equations. The inverse design analyses on multi-target, multi-state and rotor (airfoil) aerodynamic configurations in forward flight are performed respectively by using the present method, and the effectiveness of the method is identified. Finally, the inverse design method is used successfully to design a rectangular rotor with new airfoils which possesses aerodynamic characteristics similar to the UH-60A helicopter rotor with its new tip blade.

Key words: rotor, aerodynamic configuration, forward flight, inverse design, Navier-Stokes equation, airfoil

CLC Number:

ZHAO Guoqing, ZHAO Qijun. Inverse Design Analysis Method on Rotor with Advanced Aerodynamic Configuration Based upon Target Pressure Distribution[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(3): 744-755.

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Inverse Design Analysis Method on Rotor with Advanced Aerodynamic Configuration Based upon Target Pressure Distribution

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