Abstract

In this research the aerodynamic load have been determined in critical transonic speeds taking into consideration the shock wave effect along X-29 aircraft wing , first by using computational fluid dynamics in fluent program, then taking these results as an applied loads in the classical plate theory (c.p.t) to estimate these stresses depending on time and speeds of impact load as a major parameter, and a numerical method using F.E.M (Ansys 10 ) for confirming the results that obtained from analytical solution. Results shows that the value of pressure coefficient along the wing using (c.p.t) is higher then the experimental one which is more save in design for transonic flow and its appeared that the position of maximum effect of shock wave on wing section depends on angle of attack , sweep angle and duration time of the shock wave load .