战斗机进排气一体化试验数据修正方法

为提高战斗机进排气一体化试验数据准度,基于推阻划分原理,提出了一种修正进气道内流和迷宫密封压差影响的试验数据修正方法。为提高修正可靠性,在总压测量方面,采取了按流场均匀度布置测量点的方法,对流场均匀度较差区域进行测量点加密,提高了总压测量准度；在总压计算方面,采用加权平均法计算平均总压,提高了总压计算准度。为验证该修正方法,在FL-14风洞开展了某型战斗机进排气一体化试验,试验结果表明:修正方法对试验精度影响在国军标相关试验精度指标范围内；本修正方法仅适用于中等迎角以下的进排气试验数据修正；与未修正试验结果相比,修正后的全机升力线斜率和升力值减小,阻力值增加。 

Correcting method of fighter intake/exhaust test data

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.