Three approaches are suggested to verifty the Euler flow calcuations for aircraft configurations.The first proposed approach is to calculate the same flow problem on the same grid with different methods, which uses,Jameson's central-difference finite volume method and Steger-Warming's flux-splitting finite volume method.The second one is to evaluate the effects of grid refinements by using Roache's Grid Convergence Index.And the third one is to calculate the same flow problem on grids with different topology.The computed results are validated by comparisons with authoritative and credible experimental data.