Abstract
In this publication, we study the supersonic flow around a pointed airfoil in free air. The work is to develop a numerical calculation program using the relations of oblique shock waves; and Prandtl Meyer expansion of constant specific heats around a wedge to determine the characteristics of pointed airfoil in supersonic steady. This regime is characterized by the emergence of a shock wave, usually weak, which will be attached to the leading edge of the airfoil if it has a pointed shape. The airfoil is discretized into flat plate's juxtaposed one to another. It should be noted that the flow is two dimensional. In the place where there is concavity of the wall there will be shock waves and in an other place where there is convexity of the wall there will be an expansion of the flow. The latter type is of Prandtl Meyer. The flow is characterized by increases of entropy seen that there appears a shock wave. The drag is not zero. It is equal to the drag of the shock wave even though the flow is inviscid. We neglect the other components of the drag. Most authors prefer the use of the thin airfoil theory to evaluate the flow around an airfoil. A Comparison is made with this theory for thin thickness to determine a limit of applications of this theory. Applications are made for moderate thickness. The substance chosen is air.