Experimental Studies on Micro-Vortex Generator Controlled Shock/Boundary-Layer Interactions in Mach 2.2 Intake

Kaushik, Mrinal

doi:10.1007/s42405-019-00166-5

Cited by 18 publications

(7 citation statements)

References 12 publications

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“…Some of the well-established control methods used to manipulate the SBLIs are boundary layer bleed, vortex generators, streamwise slots, porous cavity, surface bump, splitter, etc. [103][104][105][106][107][108][109][110][111]. Boundary layer bleed is the widely used control technique (can be active or passive, depending on the energy requirement), where the low momentum fluids near the wall are bled and the high momentum fluids outside the boundary occupy their location.…”

Section: Passive Control Techniquesmentioning

confidence: 99%

“…The use of micro-vortex generators (MVGs) to reduce shock-induced separation has gained popularity in recent years due to their interesting result [105]. Furthermore, vortices of mixed size shed in a streamwise manner can effectively control the size of the recirculation field, according to the findings.…”

Section: Passive Control Techniquesmentioning

confidence: 99%

“…(Passive control) [105,121,[129][130][131][132][133][134][135][136][137][138][139][140][141][142][143][144] Very efficient in suppressing the separated shear layer by energizing the incoming boundary layer through vortices.…”

Section: Mvgsmentioning

confidence: 99%

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Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Jana

Kaushik

2022

Adv. Aerodyn.

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The primary focus of the present survey is to categorize the results of various investigations on the Shock/Boundary-Layer Interactions (SBLIs), their repercussions, and the effective ways to control them. The interactions of shock waves with the boundary layer are an important area of research due to their ubiquity in several applications ranging from transonic to hypersonic flows. Therefore, there is a need for a detailed inspection to understand the phenomena to predict its characteristics with certain accuracy. Considering this in mind, this article presents some key features of the physical nature of SBLIs, their consequences, and the control techniques in a sequential manner; in particular, the passive control techniques for the supersonic and hypersonic intakes are reviewed in detail.

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Section: Passive Control Techniquesmentioning

confidence: 99%

Section: Passive Control Techniquesmentioning

confidence: 99%

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Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Jana

Kaushik

2022

Adv. Aerodyn.

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“…As the flight speed range increases, it is difficult to coordinate the low-speed starting performance and the high-speed cruising performance of the ramjet, which seriously restricts the engine performance improvement [1]. In order to improve the inlet performance, many studies have been carried out on various active and passive flow control methods, such as boundary layer suction [2,3], plasma [4][5][6], vortex generators [7][8][9][10], and so on. These flow control methods could improve the shock wave/boundary layer interference and other flow field characteristics, and improve the inlet performance to a certain extent.…”

Section: Introductionmentioning

confidence: 99%

Study on a Two-Dimensional Supersonic Inlet with Inner Profile Adjustment

et al. 2022

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According to the requirements of a wide speed range, a variable-geometry supersonic inlet with inner surface adjustment is studied. The basic design model of the inlet is established, and the influence of profile adjustment on the resisting back pressure ability and inlet performance boundary are analyzed using a theoretical method. Based on the numerical simulation method, the flow field simulation is carried out, and the flow field parameter distribution and performance of the adjustment inlet are studied in comparison with the fixed-geometry scheme. The results show that the starting Mach number is not changed for two inlet schemes because they have the same profile during low-speed flight. The fixed-geometry inlet has insufficient compression on the incoming flow, and the resisting back pressure ability decreases significantly during high-speed flight. The compression ratio and the compression wave system can be easily changed at the same time through the adjustment of the inner profile for the adjustable inlet during high-speed flight. Both the theoretical analysis and numerical simulation show that the resisting back pressure ability and performance are significantly improved after the adjustment. As such, the adjustment method in this paper can fundamentally solve the problem of the insufficient compression of the wide-range working inlet during high-speed flight, and the method can be easily realized.

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“…In 2019, Kaushik reported the effectiveness of MVG in reducing SWBLI effect on a Mach 2.2 intake. His MVG was placed on the intake's external compression ramp just a small distance upstream of the throat section [23]. Verma and Manisankar also demonstrated the usefulness of vane-type vortex generators in reducing the impact of Mach reflection-induced interaction inside an intake with an internal flow of Mach 2.05 [24].…”

Section: Introductionmentioning

confidence: 99%

Potential of Micro-Vortex Generators in Enhancing the Quality of Flow in a Hypersonic Inlet-Isolator

Idris

Saad

Kontis

2020

ARFMTS

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The rush to be the first to demonstrate a practical hypersonic cruise missile has never been more frantic among the world’s superpowers, especially since China and India have also announced their own programme. The main hurdle for safe hypersonic flight is the severe shock wave-boundary layer interaction (SWBLI) that could induce flow separation. The separation could lead to inlet unstart and also structural damage at the flow re-attachment point. The simplest method to control these phenomena is by using passive flow control devices such as micro-vortex generator (MVG). The MVG is typically sized in the range of sub-boundary layer and the vortex generated can induce an early transition to turbulence thus avoiding or reducing the impact of flow separation. Many studies have been published with regard to MVG, but most were done in low supersonic speed and not in the hypersonic flow regime. In the current study, the MVG array was placed strategically at various locations on a hypersonic inlet-isolator representative geometry. The MVG has been proven to be very effective in eliminating or reducing the size of flow separation thus reducing the associated peak pressure at the re-attachment point.

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Experimental Studies on Micro-Vortex Generator Controlled Shock/Boundary-Layer Interactions in Mach 2.2 Intake

Cited by 18 publications

References 12 publications

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Survey of control techniques to alleviate repercussions of shock-wave and boundary-layer interactions

Study on a Two-Dimensional Supersonic Inlet with Inner Profile Adjustment

Potential of Micro-Vortex Generators in Enhancing the Quality of Flow in a Hypersonic Inlet-Isolator

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