Numerical Simulation Of The Composite Wing

Abstract

The composite wing design has gained more and more attention in recent years. To obtain a new aerodynamic design by giving optimal aerodynamic dimensions. Composite wing obtains high lift and high angle of attack, In this study comparison performance of four wings. Basic wings by using one airfoil for each wing, and composite wings by using two airfoils in each wing. In composite wings select two  NACA for the airfoil. The NACA: S1223-(S1223-iL) at the root gives a high lift, but the  NACA: LS0421 (IS 421-iL) at the tip gives a high angle of attack. This composite wing design was tested for the two twist angles ( from αt=0°, αt =5°) at tip wing, and mean velocity (U=40m/s). The wings are modeled using  ANSYS version ( 14)  with an appropriate turbulence model (k-w, SST). The numerical investigation involved solving the governing equations continuity, Navier –Stokes equations.  In the main results, the existing correlation between the Lift and angle of attack, Drag with an angle of attack is obtained, Also, plotting graphs for pressure coefficient, velocity and streamline distribution was obtained, it can be concluded that for maximum aerodynamic lift increasing by (16%) compare with the basic wings. The composite wing extension rang of the angle of attack by the ratio of 35% compared with a basic wing. The optimized value of the angle of attack was ( -4) and (26). That means extension in the angle range before the stall. This study gives new data on the aerodynamic design of the composite wing. Also, this design increase the drag by a small ratio (7.68%) compare with a basic wing.