In this paper Numerical simulations are performed using the control volume method to obtain separation point of two-dimensional laminar, steady, incompressible flows. Low Reynolds number flows over cylinder, NACA 0012 and NACA 633-418 airfoil are considered under the influence of an external adverse pressure gradient for different attack angles in order to examine the accuracy of the experimental Stradford s criteria. Then the Stradford s criterionis amended accurately. Numerical results compared well with those of the Stratford s criteria for NACA 633-418, NACA 0012 airfoil and cylinder.

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