Integrated supersonic wind tunnel nozzle
| Autor: | Jingang Dong, Jiang Zhang, Junmou Shen, Chen Xing, Handong Ma, Qin Yongming, Ruiqu Li |
|---|---|
| Rok vydání: | 2019 |
| Předmět: |
0209 industrial biotechnology
Supersonic wind tunnel Mechanical Engineering Airflow Nozzle Aerospace Engineering TL1-4050 02 engineering and technology Mechanics 01 natural sciences 010305 fluids & plasmas symbols.namesake Boundary layer 020901 industrial engineering & automation Mach number Inviscid flow 0103 physical sciences symbols Supersonic speed Choked flow Geology Motor vehicles. Aeronautics. Astronautics |
| Zdroj: | Chinese Journal of Aeronautics, Vol 32, Iss 11, Pp 2422-2432 (2019) |
| ISSN: | 1000-9361 |
| DOI: | 10.1016/j.cja.2019.07.005 |
| Popis: | In supersonic wind tunnels, the airflow at the exit of a convergent-divergent nozzle is affected by the connection between the nozzle and test section, because the connection is a source of disturbance for supersonic flow and the source of disturbance generated by this disturbance propagates downstream. In order to avoid the disturbance, the test can only be carried out in the rhombus area. However, for the supersonic nozzle, the rhombus region is small, limiting the size and attitude angle of the test model. An integrated supersonic nozzle is a nozzle and a test section as a whole, which is designed to weaken or eliminate the disturbance. The inviscid contour of the supersonic nozzle is based on the method of characteristics. A new curve is formed by the smooth connection between the inviscid contour and test section, and the boundary layer is corrected for the overall curve. Integrated supersonic nozzles with Mach number 1.5 and 2 are designed, which are based on this method. The flow field is validated by numerical and experimental results. The results of the study highlight the importance of the connection about the nozzle outlet and test section. They clearly show that the wave system does not exist at the exit of the supersonic nozzle, and the flow field is uniform throughout the test section. Keywords: Boundary layer, Disturbance, Flow field, Integrated supersonic nozzle, Supersonic wind tunnels, The rhombus region |
| Databáze: | OpenAIRE |
| Externí odkaz: |
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