Development of a Large Mass Flow Inlet Test System in Low Speed Wind Tunnel

被引：0

作者：

Tang B.-B. ^{[1
]}

Li C.-K. ^{[1
]}

机构：

[1] The 3rd Aerodynamic Research and Test Department, AVIC Aerodynamics Research Institute, Harbin

来源：

Tuijin Jishu/Journal of Propulsion Technology | 2018年 / 39卷 / 12期

关键词：

Ejecting; Inlet; Large mass flow; Performance measurement; Wind tunnel test;

D O I：

10.13675/j.cnki.tjjs.2018.12.024

中图分类号：

学科分类号：

摘要：

A large mass flow inlet test system was developed in the FL-8 wind tunnel to improve its test ability. According to the condition, the system was set in the center of the wind tunnel and ejected mixed air into the diffusion section without destroying the original one. The system can perform all kinds of inlet test functions including inlet flow field simulation, performance measurement, flow control and measurement. In order to verify the performance of the system, a test was carried out. Results show that the system has high measurement accuracy, ejection ability and exhaust air has little influence on the wind tunnel flow field. The flow measurement accuracy achieve 0.3% and the inlet test system achieves maximum 2.8kg/s, which leads to a 50% capacity increase and can carry out three inlet test simultaneously. © 2018, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：2839 / 2844

页数：5

共 8 条

[1] Smith A.R., Thorne R., Gouttenoire C., Et al., Aerodynamic Aspects of Application of Negative Scarf Intake to High Bypass Ratio Civil Turbofans
[2] Montetagaud F., Montoux S., Negative Scarfed Intake: Design and Acoustic Performance
[3] Arend D.J., Castner R.S., Frate F.C., Et al., A Low Cost, Compact and Versatile Rig for Integrated Inlet and Propulsion Systems Research
[4] Chima R.V., Arend D.J., Castner R.S., Et al., CFD Models of a Serpentine Inlet, Fan, and Nozzle
[5] Carter M.B., Sheay P.R., Flamm J.D., Et al., Experimental Evaluation of Inlet Distortion on an Ejector Powered Hybrid Wing Body at Take-Off and Landing Conditions
[6] Manrique J.A.H., Lorenzo M.A.G., Bouldin B., CFD Analysis and Full Scale Wind Tunnel and Flight Testing of a Complex Auxiliary Power Unit Intake System
[7] Wu J.-P., Chen J., Wang Z.-G., Experiment on Starting Performance of Multi-Nozzle Supersonic Ejector, Journal of Propulsion Technology, 29, 2, pp. 174-178, (2008)
[8] Wang G.-Z., Wu S.-S., Wang Z.-S., Et al., Effect of Mixing Tube Area and Position on Performances for Lobed Ejector, Journal of Propulsion Technology, 21, 4, (2000)

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