Conventional aircraft has a streamlined body and consist of two wings. The main concern of the designers is to improve a model efficiency by consuming less fuel and high speed for covering a certain distance. This is only possible by reducing drag force of the whole aircraft. The drag created on the wingtip of the wing for the air separation between upper and lower air is called induced drag. In this study, lift and drag coefficient will be calculated with and without winglet on the wing tip. Reynold’s Average Navier-Stokes’s simulation over Boeing 737d supercritical wing at Mach 0.74 and Reynold’s number=8.64×107 will be taken as calculated estimated data to investigate drag and lift force with the change of angle of contact (at cruising angle 0 to -5 degree). For b737d supercritical wing chord line and chamber line difference is 5% of the chord length. ANSYS Fluent is being used to perform the simulation. K-ω SST (sheer stress transport) model is used to calculate lift and drag coefficient.