Abstract:

Based on the two dynamic grid methods (spring smooth approximation method and local remeshing method) and the function/shape function method, according to the facts that the program and the parameters change frequently at the phase of aircraft conceptual design, a dynamic grid method is proposed for the shape of the 2D airfoil. The method passes the changed boundary information to the grid, so that the grid is changed accordingly. Compared with the commonly used dynamic grid method, this method has better strength and resilience of the parameters performance, so the grid is generated fast. NACA 2415 airfoil, which adopts the “class function” and “shape function” translation technique (CST), is simulated in the case of lowspeed turbulent flow under different angles of attack. The results show that the proposed dynamic grid technique can better simulate the flow characteristics of the airfoil and draw airfoil aerodynamic coefficients more accurately. The technique has good application value for parameter determination at the phase of aircraft conceptual design.

Key words: dynamic grid;airfoil;lowspeed;class function/shape function transfomation