Study of unsteadiness of shock wave boundary layer interaction using Rainbow Schlieren Deflectometry and Proper Orthogonal Decomposition

Chaganti, Narendra S.; Kurup, Arathi Laldinpuii; Ölçmen, Semih

doi:10.2514/6.2013-536

Cited by 5 publications

(3 citation statements)

References 5 publications

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“…Berry et al [25] used POD method to process time series of timeresolved schlieren images and studied the characteristic structure of supersonic rectangular jet. Chaganti et al [26] processed a time series of color schlieren images and studied the non-steadiness of shock wave/boundary layer interaction.…”

Section: Methodsmentioning

confidence: 99%

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Experimental Study on Hypersonic Double-Wedge Induced Flow Based on Plasma Active Actuation Array

Yang,

Zhao

et al. 2024

Aerospace

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The double-wedge configuration is a typical characteristic shape of the rudder surface of high-speed aircraft. The impact of the shock wave/boundary layer interaction and the shock wave/shock wave interaction resulting from the double wedge on aircraft aerodynamics cannot be ignored. The aerodynamic performance of the aircraft would be seriously affected. Accordingly, to reduce the wave drag, and to relieve the thermal load and pressure load, flow control is required for the shock wave/shock wave interaction and the shock wave/boundary layer interaction induced by the double-wedge configuration. In this paper, double-wedge shock wave/shock wave interaction is controlled by a high-energy surface arc discharge array and observed by high-speed schlieren flow field measurement at Mach 8. The 30-channel discharge array is set on the primary wedge plane, and actuation is generated. Hypersonic V shock wave/shock wave interaction is effectively controlled by the shock wave array induced by the high-energy surface arc discharge array, which makes the shock wave/shock wave interaction structure disappear or intermittent. The potential control mechanism is to reduce strong shock wave interaction by transforming the type of shock wave interaction. Therefore, the ability of plasma array actuation to control complex shock wave/shock wave interaction is verified, which provides a new method for hypersonic shock wave/shock wave interaction control.

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Section: Methodsmentioning

confidence: 99%

“…Steady-state characteristics have been studied in gray mean or root-mean-square analysis. The advantage of SPOD analysis method is to extract unsteady characteristics of flow field [26].…”

Section: Methodsmentioning

confidence: 99%

Experimental Study on Hypersonic Double-Wedge Induced Flow Based on Plasma Active Actuation Array

Yang,

Zhao

et al. 2024

Aerospace

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“…However, almost all the studies by rainbow schlieren deflectometry have been applied for free jet issued from nozzles. To the authors' knowledge, Chaganti et al [8] was for the first time applied a rainbow schlieren deflectometry for internal shock containing flows to understand the physics of the shock-wave boundary-layer interaction. However, their rainbow schlieren technique does not have accurate enough to describe the density field of the shock wave boundary layer interaction.…”

Section: Introductionmentioning

confidence: 99%

Two-dimensional quantitative visualization of isolator shock trains by rainbow schlieren deflectometry

et al. 2018

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Abstract. The rainbow schlieren deflectometry is effective in studying quantitatively the density fields in shock-containing free jets at high precision and high spatial resolution. However, there has been no practical application of rainbow schlieren deflectometry for shock trains in a confined duct. Therefore, in the present study, the rainbow schlieren deflectometry is applied to the flow field including a shock train in a constantarea duct where just upstream of the shock train the freestream Mach number is 1.34, the unit Reynolds number is 5.39 × 10 7 m -1 , and the boundary layer displacement thickness is 0.149 mm. As a result, a twodimensional density field of the shock train is for the first time quantitatively displayed and the fine structure of the shock train is illustrated as a color gradation representation.

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Suppressing unsteady motion of shock wave by high-frequency plasma synthetic jet

Luo

Liang

et al. 2021

Chinese Journal of Aeronautics

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Study of unsteadiness of shock wave boundary layer interaction using Rainbow Schlieren Deflectometry and Proper Orthogonal Decomposition

Cited by 5 publications

References 5 publications

Experimental Study on Hypersonic Double-Wedge Induced Flow Based on Plasma Active Actuation Array

Experimental Study on Hypersonic Double-Wedge Induced Flow Based on Plasma Active Actuation Array

Two-dimensional quantitative visualization of isolator shock trains by rainbow schlieren deflectometry

Suppressing unsteady motion of shock wave by high-frequency plasma synthetic jet

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