Application of Vortex Control to an Automotive Transcritical R744 Ejector Cycle

2018 ◽  
Author(s):  
Jingwei Zhu ◽  
Stefan Elbel
Keyword(s):  
Vortex Control ◽  
Ejector Cycle

Liutex-based vortex control with implications for cavitation suppression

2021 ◽  
Vol 33 (1) ◽  
pp. 74-85
Author(s):  
Yi-qian Wang ◽  
Hai-dong Yu ◽  
Wei-wen Zhao ◽  
De-cheng Wan
Keyword(s):  
Vortex Control

Wing tip vortex control using synthetic jets

2006 ◽  
Vol 110 (1112) ◽  
pp. 673-681 ◽  
Author(s):  
P. Margaris ◽  
I. Gursul
Keyword(s):  
Synthetic Jet ◽  
Synthetic Jets ◽  
Tip Vortex ◽  
Particle Image Velocimetry System ◽  
Driving Frequency ◽  
Velocity Measurements ◽  
Vortex Control ◽  
Image Velocimetry ◽  
Wing Tip ◽  
Jet Blowing

AbstractAn experimental investigation was conducted to study the effect of synthetic jet (oscillatory, zero net mass flow jet) blowing near the wing tip, as a means of diffusing the trailing vortex. Velocity measurements were taken, using a Particle Image Velocimetry system, around the tip and in the near wake of a rectangular wing, which was equipped with several blowing slots. The effect of the synthetic jet was compared to that of a continuous jet blowing from the same configurations. The results show that the use of synthetic jet blowing is generally beneficial in diffusing the trailing vortex and comparable to the use of continuous jet. The effect was more pronounced for the highest blowing coefficient used. The driving frequency of the jet did not generally prove to be a significant parameter. Finally, the instantaneous and the phase-locked velocity measurements helped explain the different mechanisms employed by the continuous and synthetic jets in diffusing the trailing vortex.

VORTEX CONTROL FOR TAIL BUFFET ALLEVIATION ON A TWIN-TAIL FIGHTER CONFIGURATION

1989 ◽  
Author(s):  
Dhanvada M. Rao ◽  
C. K. Puram ◽  
Gautam H. Shah
Keyword(s):  
Vortex Control ◽  
Tail Buffet

Vortex control over sharp-edged slender bodies

1995 ◽  
Vol 32 (4) ◽  
pp. 739-745 ◽  
Author(s):  
D. Gangulee ◽  
T. Terry Ng
Keyword(s):  
Vortex Control ◽  
Slender Bodies

Vortex Control

1971 ◽  
pp. 137-155 ◽  
Author(s):  
M. T. Landahl ◽  
S. E. Widnall
Keyword(s):  
Vortex Control

Air Entrainment Studies for a Supersonic Micro-Ejector System

2008 ◽  
Author(s):  
George Papadopoulos ◽  
Jason Tyll ◽  
Alan Drake ◽  
Randy Chue ◽  
John D. Williams ◽  
...  
Keyword(s):  
Air Entrainment ◽  
Combustion System ◽  
Propulsion Systems ◽  
The Past ◽  
Primary Fluid ◽  
High Vapor ◽  
Ejector System ◽  
The 1960S ◽  
Micro Combustor ◽  
Ejector Cycle

Micro-ejectors offer a unique way of entraining relative large quantities of air without any moving parts, which when mixed with fuel can provide the necessary fuel-air mixture to power a micro-combustion system. Together, the micro-ejector and the micro-combustion systems can make up components of a unique air-breathing propulsion system. Larger scale ejector-based propulsion systems that operate a rocket ejector cycle have been constructed and operated in the past, dating back to the 1960s. Only very recently this same ejector system has been scaled down to the micro-size domain for use in applications other than propulsion, more specifically as a way of entraining and mixing fuel and air for use in micro-combustor applications. The present study involved the use of propane as ejector primary fluid, chosen for its high vapor pressure which allowed us to operate a March 2 nozzle with a throat height of 31 microns under high pressure and thus achieve various degrees of air entrainment based on the area ratio between the primary nozzle and ejector secondary duct. Experimental data showed the performance of the ejector system under the various area ratios studied. The degree of mixing of the primary jet is reviewed, specifically as it pertains to air entrainment performance.

Passive Wingtip Vortex Control by Using Tip-Mounted Half Delta Wings in Ground Effect

2019 ◽  
Vol 142 (2) ◽  
Author(s):  
Anan Lu ◽  
Tim Lee
Keyword(s):  
Vortex Flow ◽  
Ground Effect ◽  
Tip Vortex ◽  
Secondary Vortex ◽  
Flow Properties ◽  
Delta Wings ◽  
Vortex Control ◽  
Physical Mechanisms ◽  
Induced Drag ◽  
Wingtip Vortex

Abstract The ground effect on the wingtip vortex generated by a rectangular semiwing equipped with tip-mounted regular and reverse half delta wings was investigated experimentally. The passive tip vortex control always led to a reduced lift-induced drag as the ground was approached. In close ground proximity, the presence of the corotating ground vortex (GV) added vorticity to the tip vortex while the counter-rotating secondary vortex (SV) negated its vorticity level. The interaction of the GV and SV with the tip vortex and their impact on the lift-induced drag were discussed. Physical mechanisms responsible for the change in the vortex flow properties in ground effect were also provided.

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