Numerical simulation of a new spoiler on upper surface of Clark Y14 wing

Abstract

Spoilers are one type of devices that used to reduce the lift on the aircraft wing. A theoretical and numerical study involves simulation of the flow behaviour around of airfoil type (Clark y-14) for the wing section are carried out. ANSYS14 software is used to solve the governing equation in three dimensions steady incompressible turbulent regime with appropriate turbulent model (k – ω, SST). In this study the lift and drag for different angles of attack, with and without spoiler effect on distribution of pressure and velocity distribution on the wing surface are steadied. A constant velocity 40 m/s is used on the wing with and without new spoiler have different cord (10% C) and (15% C) and angles of attack from -8° to +18°. The wing model is rectangular with (30 cm span and 9 cm cord). Wing has aspect ratio 30/9 and a maximum thickness of 14 % of the wing chord. A trial and error for five-gaps between spoiler and wing (0%, 2.77%, 3.33%, 3.88% and 6.66% of the wing cord)are carried out when is the wing cord is equal to 9 cm and for different gaps (0,2.5, 3, 3.5and 6 mm). Theoretical results indicated when is location spoiler 50%C, δ = 0, new spoiler cord (HI) 10%C and gap between new spoiler and wing equal 3.33%C which increase maximum lift theoretically to (28.29%) compared with clean wing.