CFD v.s wind tunnel in airfoil
 

I tried to compare CFD¡¦s results with wind tunnel test in pressure coefficient(Cp) for a developed airplane with a symmetric airfoil . At trailing edge, CFD proved that uppersurface¡¦s Cp and lowersurface¡¦s Cp close to each other ; but, the results of wind tunnel test speaded apart each other. The wind tunnel test of F-16 ran the same conclusion.Why? Thought W/T only had finit pressureholes , the curves couldn¡¦t diverge at trailing edge. According to Kutta condition, Cp curves of up/low surfaces at trailing edge must meet each other. Were W/T data incorrect ?