This paper presents the examination of Aerodynamics flying wing configuration using Computation fluid dynamics (CFD) techniques. The parameters of aerodynamic such as coefficient of drag, coefficient of lift, moment coefficient and pressure coefficient are calculated by CFD. The aerodynamic parameters are determined for different angles of attack and Mach number so that deviation of salient aerodynamic parameters can be observed and analyzed. In this work, Solution is obtained for all aerodynamic parameters by considering the effect of external flow over flying wing configuration. In this research work parameter are stall speed, stall angle of attack, drag divergence Mach number and critical Mach number. These parameters are obtained for every test case and the comparison is made between tested results and available experimental results.