Abstract: The paper describes a numerical method for evaluation of the three-dimensional inviscid supersonic flow about the re-entry vehicles of non-symmetrical bodies. The method is devoted to determining the initial-boundary value problem for hyperbolic partial differential equations in the conservation law form. The MacCormack' s explicit finite-difference schemes with second order accuracy is adopted. For a bent sphere-cones, different oriented cylindrical coordinate systems are used in different cone regions. The computation of the body surface points is different from reference[ 1,2].The numerical examples of the bent sphere-cones and the re-entry vechicles with control flaps have been worked out to demonstrate the capability of this technique. The accuracy of the results has been examined.