Research of three different civil aviation turbine engine nacelle profiles by high speed wind tunnel test and numerical simulation method was finished

and the static pressure distribution and induct performance of nacelle were obtained. By comparing the result of wind tunnel test with the numerical simulation

it showed that nacelle upside cowl would have separation when the mass flow rates reduced or the attack angle increased; the induct of downside would have separation when the mass flow rates increased; the numerical simulation result of static pressure distribution coincided with the wind tunnel result when there was no separation

but when mass flow rate reduced

the CFD results were separated before the test.