Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Lu, Frank K.; Pierce, Adam J.; Shih, Yusi; Liu, Chaoqun; Li, Qin

doi:10.2514/6.2010-4463

Cited by 22 publications

(21 citation statements)

References 46 publications

(72 reference statements)

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“…These ring structures propagate further downstream and interact with the impinging shock wave, eventually distorting the structure of the shock wave hence reducing its strength [15]. The experiments of Lu et al [16,17] and Sun et al [18] corroborated the numerical findings of Li & Liu [9,10] and identified the existence of the vortex rings, however they were not able to shed any light on the effect of the interaction between the vortex rings with the impinging shock wave.…”

Section: Introductionmentioning

confidence: 96%

Micro-Ramps for Hypersonic Flow Control

et al. 2012

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Shock/boundary layer interaction (SBLI) is an undesirable phenomenon, occurring in high-speed propulsion systems. The conventional method to manipulate and control SBLI is using a bleed system that involves the removal of a certain amount of mass of the inlet flow to control boundary layer separation. However, the system requires a larger nacelle to compensate the mass loss, larger nacelles contribute to additional weight and drag and reduce the overall performance. This study investigates a novel type of flow control device called micro-ramps, a part of the micro vortex generators (VGs) family that intends to replace the bleed technique. Micro-ramps produce pairs of counter-rotating streamwise vortices, which help to suppress SBLI and reduce the chances of flow separation. Experiments were done at Mach 5 with two micro-ramp models of different sizes. Schlieren photography, surface flow visualization and infrared thermography were used in this investigation. The results revealed the detailed flow characteristics of the micro-ramp, such as the primary and secondary vortices. This helps us to understand the overall flow physics of micro-ramps in hypersonic flow and their application for SBLI control.

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Section: Introductionmentioning

confidence: 96%

Micro-Ramps for Hypersonic Flow Control

et al. 2012

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“…2(a)), and it was then proposed as an imprint of an additional secondary vortex. The following experiment carried out by Lu et al [12] confirmed the separation regions by surface flow visualization using bands of fluorescent mixture (see Fig. 1(b)).…”

Section: Introductionmentioning

confidence: 87%

“…However, less focus has been placed on the smaller scale structures in the flow close to the micro-ramp. A few forgoing studies have investigated the flow that takes place around the micro-ramp [10,12]. Among those explorations, a common observation is the flow separation at the junction between the micro-ramp trailing edge and the flow floor.…”

Section: Introductionmentioning

confidence: 99%

The Vortical Structures in the Rear Separation and Wake Produced by a Supersonic Micro-Ramp

Liu

Sun

Wang

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This is the accepted version of the paper.This version of the publication may differ from the final published version. Permanent repository link AbstractThe vortical structures in the rear separation and wake region produced by a micro-ramp that immersed in a supersonic turbulent boundary layer are investigated. The small scale separation close to the trailing edge was reveled and this confirms the previous experimental observation. Between the reverse region and surrounding fast moving flow, a three-dimensional shear layer was formed, and vortices are generated. By using vortex line method, the spiral points were understood as the cross-sections of the Ω-shaped vortices that follow the shape of the separation. The vortical structure was analogous to that in the wake region, where similar Ω-shaped vortex can be observed which follows the deficit region caused by the micro-ramp. Finally, the revealed flow topology was conceived beneficial to studying the wall bounded turbulence which involves similar vortical structures but in a smaller scale, while the vortical pattern in the current micro-ramp wake is larger.

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“…The vortex can be clearly seen being formed at the edges of each triangle. Visualization of the Created vortex on MVGs is difficult due to unsteady nature of the flow at the region where the vortex is created [4]. …”

Section: Flow Visualisationmentioning

confidence: 99%

Parametric investigation of boundary layer control using triangular micro vortex generators

Bagheri

Muslmani

Masood

et al. 2014

EPJ Web of Conferences

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Abstract. Improving the aerodynamic performance of an airfoil is one of the primary interests of the Aerodynamicists. Such performance improvement can be achieved using passive or active flow control devices. One of such passive devices having a compact size along with an effective performance is the Micro Vortex Generators (MVGs). A special type of MVGs, which has been recently introduced in the aerospace industry, is "Triangular Shape" MVGs and its impact on aerodynamic characteristics is the main interest of this study. This study will compare the effects of various configurations through which delay of the flow separation using boundary layer control will be analysed by experimental and theoretical approach. The experimental investigations have been conducted using subsonic wind tunnel and the theoretical analysis using ANSYS® 13.0 FLUENT of which the final results are compared with each other.

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Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Cited by 22 publications

References 46 publications

Micro-Ramps for Hypersonic Flow Control

Micro-Ramps for Hypersonic Flow Control

The Vortical Structures in the Rear Separation and Wake Produced by a Supersonic Micro-Ramp

Parametric investigation of boundary layer control using triangular micro vortex generators

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