A numerical method has been developed to solve the three dimensional Navier-Stokes equations and the numerical procedure uses Osher-Chakraverthy's TVD scheme for the inviscid flux and central difference scheme for the viscous flux. LU-SSOR method is used to solve the resulting systems of discretized equations and the Baldwin-Lomax turbulent model is used. Numerical solutions of three dimensional hypersonic jet interaction flow field with angle of attack of 5° is obtained and experimentally validated this numerical result at KD-01 gun wind tunnel. By validating, some problems of numerical simulation are studied.