Abstract: An experimental study was performed to investigate the lift and drag coefficient of multiple wing. Most of the previous works carried out to increase the lift force and reduce the drag force having the more efficient and effective design. The aim of this project is to investigate the effect of multiple wings on lift and drag force. To perform this investigation a model of multiple wings is constructed and experiments were conducted in subsonic wind tunnel. The model of NACA 0012 symmetric airfoil with chord length of 21cm, maximum thickness 0.12cm, span length 21cm was selected for tri- plane configurations. The aerodynamic characteristics were examined placing multiple wings 12cm apart at low speed condition with various angles of attack like 0, 5,10,15,20 degrees for all the tri plane configurations. The ideal and experimental lift and drag coefficient is measured based on the experimental data. From this experimental investigation it shows that the coefficient of pressure and lift, both are increased with the angle of attack, on the other hand, drag coefficient is slightly decreased.