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引射短舱可以模拟发动机短舱的喷流影响,并部分模拟进气影响,能用于研究发动机短舱与机翼及增升装置的气动干扰特性,且具有研制周期短、造价低等特点,是在风洞中开展飞机/发动机一体化设计研究的一种重要试验技术。本文介绍了气动中心低速所在引射短舱设计技术和试验技术方面的新进展。采用商业软件对引射短舱进行了三维流场数值模拟,获得了引射短舱性能和三维流场信息。对引射短舱内部流场进行了分析和研究,对引射喷嘴数量、位置进行了优化,增加了引射短舱的进气流量,改善了尾喷口流场均匀度,明显提高了引射短舱性能。发展了空气桥技术,采用有限元方法进行了优化设计,对空气桥和天平进行一体化设计,并进一步发展了空气桥影响修正技术,解决了供气管路对天平测力的影响问题。发展了高精度流量测量控制技术,采用了数字阀、流量控制单元、短舱内部测量耙等技术,提高了流量的控制测量精度及测量不确定度,流量控制精度达到了0.1%,流量测量不确定度达到了0.3%,引射短舱落压比控制精度优于0.01。研制了短舱移动支撑装置,能够实现引射短舱的独立支撑,并实现短舱前后和上下位置的变化,用于开展短舱位置优化研究。最后,介绍了引射短舱的地面性能测试及风洞试验应用,给出了性能测试与数值模拟的对比结果和典型的风洞试验结果,试验结果表明动力影响使得飞机0°迎角升力减小,升力线斜率增大,失速迎角推迟。
The nacelle can simulate the jet flow of engine nacelles and partially simulate the influence of air intake. It can be used to study the aerodynamic interference characteristics of nacelles, wings and lifting devices, and has the characteristics of short development cycle and low cost , Is an important test technique for aircraft / engine integrated design research in wind tunnel. This article describes the recent developments in the design and test techniques for the injection nacelle where the low velocity of the pneumatic center is located. The commercial software was used to simulate the three-dimensional flow field of the induced nacelle, and the information of the behavior of the induced nacelle and the three-dimensional flow field were obtained. The flow field inside the shot nacelle is analyzed and studied. The number and position of the shot nozzle are optimized, the intake flow of the shot nacelle is increased, the flow field uniformity at the tail nozzle is improved, Nacelle performance. The air bridge technology was developed. The finite element method was used to optimize the design. The air bridge and the balance were integrated. The air bridge influence modification technology was further developed to solve the problem that the air supply pipeline affected the balance force measurement. The development of high-precision flow measurement and control technology, the use of digital valves, flow control unit, the nacelle measuring rake and other technologies to improve the control flow measurement accuracy and measurement uncertainty, flow control accuracy of 0.1%, flow measurement is not The degree of certainty reached 0.3%, and the control accuracy of the drawdown nip ratio was better than 0.01. The nacelle movement support device was developed to realize the independent support of the launch nacelle and realize the change of the nacelle before, after and up and down for the optimization of the nacelle position. Finally, the ground performance test and wind tunnel test application of the induced draft nacelle are introduced. The comparison between the performance test and the numerical simulation and the typical wind tunnel test results are given. The experimental results show that the dynamic influence of the aircraft at 0 ° angle of attack lift Small, lift line slope increases, stalling angle of attack postponed.