In order to improve the accuracy of the fighter intake/exhaust test results

a method based on the principle of thrust and drag bookkeeping

which can be used in correcting the effects of inlet internal flow and labyrinth seal pressure difference

was presented. Two measures were used to increase the liability of the correcting method: total pressure measurement points were distributed by the flow field

particularly intensive on nonevent area; the total pressure was calculated with weighted average method. In order to verify the correcting method

a fighter intake/exhaust test was conducted in the FL-14 wind tunnel. The test results indicate that

the impact of correcting method on testing accuracy is within the index of GJB; the correcting method can only be used within the medium angle of attacks; with the use of internal flow effects correction

the lift slope and the lift itself decreases

while the drag increases.