An experimental investigation was conducted on the discharge coefficient of multi-holes cooling with different inclined angles in the curved wall for an aircraft engine combustor.The research purpose is to obtain the tendency of the average discharge coefficients with the pressure parameter

one of the most important influencing factors

and to analyze the flow dynamics.The research results indicate that as an aerodynamics factor the pressure parameter has significant impact on the discharge coefficient of the discrete holes for a given geometrical configuration

and for different inclined angles it has different effects.