收敛型引射喷管/后体风洞试验研究

本试验在600mm×600mm跨超音速风洞里进行。从图1看出,高压空气通过空心支架进入高压室,然行经四个径向音速喷咀膨胀进入低压室。在音速喷咀环,端盖,活动内套之间有一对金属波纹管来密封。从低压室来的空气分成两股流:主流经四个空心整流支板的扇形空间;次流经限流喷咀穿过支板内部翼型通道,进入环形次流腔,最后和主流汇合喷出。

EXPERIMENTAL INVESTIGATION OF CONVERGENT EJECTOR NOZZLE/AFTERBODY IN WIND TUNNEL

The work is aimed at determining the overall installation performance of the convergent ejector nozzle/afterbody with or without fixed auxiliary inlet doors. The experimental mach numbers range from 0.6 to 1.2. The nozzle pressure ratio extends from 2.6 to 4.3. The corrected secondary weight flow ratio is 3.5%. The testing technique presented gives the correlation of the axial momentum tare forces of bellows with the pressure measured in the bellows. The wind tunnel test data can be revised in timely manner with the tare forces computed. The tests show that due to the effect of the tertiary flow the nozzle thrust coefficient and efficiency of the ejector nozzle with fixed auxiliary inlet doors increase by 1 to 1.6% and 1.6 to 2.8% respectively compared with one without these doors.