Supervisor:
Southwest Ordnance Industry Bureau
Organizer:
Chongqing Ordnance Industry Society
Chongqing University of Technology
Chongqing University of Technology
Aerodynamic analysis and optimization of trailing edge variable camber airfoil under large deflection angle
| DOI: | 10.11809/bqzbgcxb2024.11.020 |
| Keywords: | curvature of trailing edge; large deflection angle; laminar airfoil; multi island genetic algorithm; lift to drag ratio |
| Abstract: | In order to study the aerodynamic variation law of trailing edge variable camber wing under large deflection angle, taking the laminar airfoil NACA63a612 as example, effects of Mach number and angle of attack on the aerodynamic characteristics of airfoil with a wide range of deflection angles at the trailing edge are investigated by using N S equation and S A turbulence model.An airfoil optimization method based on multi island genetic algorithm is proposed.Taking the optimal lift coefficient and lift to drag ratio as the optimization objectives, the optimization model of trailing edge variable camber airfoil is established.The results show that the increase of the trailing edge deflection angle decrease the critical Mach number and the critical angle of attack.When the Mach number is 0.6 and the deflection angle is 10°, the shock wave begins to appear on the upper wing surface, and the shock wave moves backward with the increase of velocity.The larger deflection angle of the trailing edge can improve the lift coefficient, the drag coefficient increases, the lift drag ratio decreases, and the small angle deflection prompts better aerodynamic benefits.Optimal aerodynamic characteristic is achieved when the cruising speed is 0.6 Ma and the trailing edge deflection angle is 2.9°, the lift coefficient is increased by 48.6%, and the lift to drag ratio is increased by 9.8%.The research results provide a reference for the research and optimization design of the aerodynamic characteristics of variable camber wings. |
| Published: | 2024-11-30 |