Propulsion innovations have been the fundamental driver for progress in air traortation. Air traortation in the new millennium will require revolutionary solutions to meet public demand for improving safety, reliability, environmental compatibility and affordability. NASA has developed a research direction aimed at developing aeropropulsion technologies that will revolutionize the aviation industry to achieve an air traortation system that meet the above objectives. These revolutions are: the gas turbine revolution, the engine configuration revolution, the fuel infrastructure revolution, and the alternate energy and power revolution. This study is concentrated on distributed propulsion that is a concept of second revolution. A twin-engine, low-wing traort model, with a supercritical wing designed for Mach number of 0.77 and lift coefficient of 0.55 is used. For the purpose of solving the flow around this aircraft a commercial code is used and results for various conditions, like pressure coefficient in the wing sections and pressure contours and velocity contours and important aerodynamic curves, are presented. These results have been compared with the experimental results, and the effects of the number of computational cells and the effect of turbulence models have been studied. In the next step engines are distributed from 1 engine on each wing to 8 engine and the effects on the aircraft drag force have been evaluated. Drag Analysis shows that propulsion system drag force is decreased from 15.2 percent of aircraft total drag to 8.2 percent, and simultaneously wing drag force is increased from 51.7 percent of aircraft total drag upto 57.8 percent. Finally the net effect is increment in aircraft total drag by 2 percent to 4 percent with respect to number of engines that used, and the main source of these changes is pressure drag component. The governing equations in these problems are the Navier-Stokes equations. The Reynolds averaging technique is used to average the equations and the Shear-Stress Transport ?-? and Spalart-Allmaras model is used to model the turbulence behavior of the flow field. The Reynolds averaged equations are integrated in the control volumes shaped around the model body and the resulting equations are discredited into a set of algebraic equations and are solved in coupled manner. The hybrid grid is used, and in the inner region of the domain the grid system is unstructured and in the outer region of domain grid is structured