摘要
To gain high efficiency for the simulation of the aerodynamic characteristics of the rotor in hover,body?fitted momentum source(BFMS)method is proposed.In this method,the actual blade geometry is represented by the single layer of volume grid surrounding the blade.Aiming at correctly simulating the aerodynamic characteristics of the discrete cells along the chordwise of blade airfoil section,a new distributed force model is proposed.For comparison,the RANS method with S?A turbulence model and the steady rotor momentum source(SRMS)method based on embedded grid systems are established,respectively.And the grid connecting methodology is improved to embed the blade into the background grids for the three methods.Then,simulations are performed for the hovering Caradonna?Tung rotor by these methods,and the calculated results are compared with the available experimental data.Moreover,the pressure distributions along the blade are compared with the conventional momentum source methods.It is demonstrated that the BFMS method can be employed as an effective approach to predict rotor aerodynamic characteristics with a low computational resource and reasonable accuracy.
To gain high efficiency for the simulation of the aerodynamic characteristics of the rotor in hover,body-fitted momentum source(BFMS)method is proposed. In this method,the actual blade geometry is represented by the single layer of volume grid surrounding the blade. Aiming at correctly simulating the aerodynamic characteristics of the discrete cells along the chordwise of blade airfoil section,a new distributed force model is proposed. For comparison,the RANS method with S-A turbulence model and the steady rotor momentum source(SRMS)method based on embedded grid systems are established,respectively. And the grid connecting methodology is improved to embed the blade into the background grids for the three methods. Then,simulations are performed for the hovering Caradonna-Tung rotor by these methods,and the calculated results are compared with the available experimental data. Moreover,the pressure distributions along the blade are compared with the conventional momentum source methods. It is demonstrated that the BFMS method can be employed as an effective approach to predict rotor aerodynamic characteristics with a low computational resource and reasonable accuracy.
基金
supported by the Qian Xuesen Innovation Foud of China Aerospace Science and Technolygy Corporation
