摘要
An Euler solver is developed for calculating the flowfield around the propeller. The Euler equations are recast in the blade attached rotating coordinate system with absolute flow variables.The finite volume explicit Runge Kutta time stepping scheme is employed for solving the equations.The presented method is applied for a two bladed propeller NACA10 (3) (066) 033.An algebraic O O grid is generated. Comparison of the mumerical results shows good agreement with the experimental data.
An Euler solver is developed for calculating the flowfield around the propeller. The Euler equations are recast in the blade attached rotating coordinate system with absolute flow variables.The finite volume explicit Runge Kutta time stepping scheme is employed for solving the equations.The presented method is applied for a two bladed propeller NACA10 (3) (066) 033.An algebraic O O grid is generated. Comparison of the mumerical results shows good agreement with the experimental data.
