In the case of micro-channels, the boundary layer is formed on the walls and it plays a role of a wall of a converging and diverging nozzle. Then, the outlet Mach number is beyond unity even if the tube is straight. Therefore, in the present study, the successive incident and reflected shock waves on underexpanded state jet from a straight micro-tube whose diameter ranges from 150μm to 500μm were visualized by Schlieren and Shadowgragh methods. The stagnation pressure ranges from 597 to 963 kPa. The flow characteristics on supersonic jet at the micro-tube outlet were also obtained. Also, it is confirmed that Mach number at a straight micro-tube outlet is beyond unity since the shock wave generates from the needle and the Mach number fluctuates in the jet. The experimental correlation for the distance from the micro-tube outlet to the Mach disk as a function of the ratio of stagnation pressure to ambient back pressure was proposed and compared with available correlations in literature.
Skip Nav Destination
ASME 2010 8th International Conference on Nanochannels, Microchannels, and Minichannels collocated with 3rd Joint US-European Fluids Engineering Summer Meeting
August 1–5, 2010
Montreal, Quebec, Canada
Conference Sponsors:
- Fluids Engineering Division
ISBN:
978-0-7918-5450-1
PROCEEDINGS PAPER
Flow Structure of Supersonic Jet From a Straight Micro-Tube Available to Purchase
Chungpyo Hong,
Chungpyo Hong
Tokyo University of Science, Noda, Chiba, Japan
Search for other works by this author on:
Yasuhiro Yoshida,
Yasuhiro Yoshida
Hitachi Ltd., Hitachi, Ibaraki, Japan
Search for other works by this author on:
Yutaka Asako,
Yutaka Asako
Tokyo Metropolitan University, Hachioji, Tokyo, Japan
Search for other works by this author on:
Koichi Suzuki
Koichi Suzuki
Tokyo University of Science, Yamaguchi, Sanyo-Onoda, Yamaguchi, Japan
Search for other works by this author on:
Chungpyo Hong
Tokyo University of Science, Noda, Chiba, Japan
Yasuhiro Yoshida
Hitachi Ltd., Hitachi, Ibaraki, Japan
Yutaka Asako
Tokyo Metropolitan University, Hachioji, Tokyo, Japan
Koichi Suzuki
Tokyo University of Science, Yamaguchi, Sanyo-Onoda, Yamaguchi, Japan
Paper No:
FEDSM-ICNMM2010-30622, pp. 467-473; 7 pages
Published Online:
March 1, 2011
Citation
Hong, C, Yoshida, Y, Asako, Y, & Suzuki, K. "Flow Structure of Supersonic Jet From a Straight Micro-Tube." Proceedings of the ASME 2010 8th International Conference on Nanochannels, Microchannels, and Minichannels collocated with 3rd Joint US-European Fluids Engineering Summer Meeting. ASME 2010 8th International Conference on Nanochannels, Microchannels, and Minichannels: Parts A and B. Montreal, Quebec, Canada. August 1–5, 2010. pp. 467-473. ASME. https://doi.org/10.1115/FEDSM-ICNMM2010-30622
Download citation file:
9
Views
Related Proceedings Papers
Supersonic Flow at Micro-Tube Outlet
IMECE2009
Related Articles
An Experimental Study on the Influence of Vortex Generators on the Shock-Induced Boundary Layer Separation at M = 1.4
J. Appl. Mech (July,2009)
Detailed Flow Study of Mach Number 1.6 High Transonic Flow With a Shock Wave in a Pressure Ratio 11 Centrifugal Compressor Impeller
J. Turbomach (October,2004)
Propagation and Decay of Shock Waves in Turbofan Engine Inlets
J. Turbomach (January,2005)
Related Chapters
Antilock-Braking System Using Fuzzy Logic
International Conference on Mechanical and Electrical Technology, 3rd, (ICMET-China 2011), Volumes 1–3
A Simple Carburetor
Case Studies in Fluid Mechanics with Sensitivities to Governing Variables
Investigation on Cavitating Flow of a Novel High Pressure Nozzle with Grooved Needle
Proceedings of the 10th International Symposium on Cavitation (CAV2018)