Wind tunnel experiments were carried out in a subsonic wind tunnel in Fluid Mechanics Laboratory at MITCOE, Pune. The objective of this research was to compare the experimental coefficient of lift and drag for a NACA 2412 airfoil with that for NACA 2412 airfoil with internal passage. Both the airfoils were of same dimensions and profile. The chord length (c) was 100 mm and the span (b) was 100 mm. The range of free stream velocity measured upstream with Pitot tube was in the range of 8 to 18ss m/s. The density of air was taken to be 1.2 kg/m3. Experimental results indicate that the lift coefficient for 3D NACA 2412 airfoil with internal passage was marginally higher than the lift coefficient for 3D NACA 2412. We can conclude that point of separation for 3D NACA 2412 airfoil with internal passage is shifted towards trailing edge. This reduces the boundary layer separation at higher angle of attack from the airfoil. The range of angle of attack (α) was between zero and 40°.