Transient behavior of shock train with and without controlling

Chen, Zhi; Yi, Shihe; Ahmed, Noor A.; Kong, Xiao ping; Quan, Peng cheng

doi:10.1016/j.expthermflusci.2015.03.010

Cited by 8 publications

(5 citation statements)

References 41 publications

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“…Their experimental results suggest that inlet unstart can be delayed or avoided by controlling the boundary layer on the inlet walls. The fine flow structures of the unstart shock train in an isolator flow were also revealed by Chen et al [18,19] by performing nano-tracer planar laser scattering (NPLS), which makes it well-suited for studying the flow mechanism.…”

Section: Introductionmentioning

confidence: 88%

Correlation Analysis of Separation Shock Oscillation and Wall Pressure Fluctuation in Unstarted Hypersonic Inlet Flow

et al. 2019

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The flow field in a hypersonic inlet model at a design point of M = 6 has been studied experimentally. The focus of the current study is to present the time-resolved flow characteristics of separation shock around the cowl and the correlation between the separation shock oscillation induced by the unstart flow and the wall pressure fluctuation when the inlet is in a state of unstart. High-speed Schlieren flow visualization is used to capture the transient shock structure. High-frequency pressure transducers are installed on the wall around both the cowl and isolator areas to detect the dynamic pressure distribution. A schlieren image quantization method based on gray level detection and calculation is developed to analyze the time-resolved spatial structure of separation shock. Results indicate that the induced separation shock oscillation and the wall pressure fluctuation are closely connected, and they show the same frequency variation characteristics. The unsteady flow pattern of the “little buzz” and “big buzz” modes are clarified based on time-resolved Schlieren images of separation shock. Furthermore, the appropriate location of the pressure transducers is determined on the basis of the combined analysis of fluctuating wall-pressure and oscillating separation shock data.

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Section: Introductionmentioning

confidence: 88%

Correlation Analysis of Separation Shock Oscillation and Wall Pressure Fluctuation in Unstarted Hypersonic Inlet Flow

et al. 2019

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“…Santhosh Kumar Gugulothu 1 *, B. Bhaskar 2 and V.V. Phani Babu 3 1 Department of Mechanical Engineering, National Institute of Technology, Andhra Pradesh, India…”

Section: Author Detailsmentioning

confidence: 99%

“…When the pressure introduced in the reverse direction of the combustor zone obtained the variation in pressure from the isolator and combustor. The difference between isolator and combustor zone is adjusted by changing the shock wavelength [3]. While designing the isolator, need serious concern about the unstart phenomenon.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles

Gugulothu¹,

Bhaskar²,

Babu³

2020

Numerical and Experimental Studies on Combustion Engines and Vehicles

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Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with compressible fluid flow by considering the density-based solver with standard K-ε turbulence model. The species transport model with single step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in open literature. The obtained results show that the variation of the divergence angle and back pressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the back pressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also moves towards the leading edge of the isolator leading to rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced back pressures.

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“…The difference between the isolator and combustor zone is adjusted by changing the shock wavelength. 3 While designing an isolator, there should be a serious concern about the unstart phenomenon. An isolator may have severe effects due to high speed in the flight.…”

Section: Introductionmentioning

confidence: 99%

“…When the pressure is introduced in the reverse direction of the combustor zone, the obtained variation in pressure from the isolator and combustor are considered. The difference between the isolator and combustor zone is adjusted by changing the shock wavelength 3 . While designing an isolator, there should be a serious concern about the unstart phenomenon.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic investigation of the shock train in a scramjet with the effects of backpressure and divergent angles

Gugulothu

2020

Heat Trans

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Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of a shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify the two-dimensional Reynolds-averaged Navier-Stokes equation with the compressible fluid flow by considering the densitybased solver with the standard k-ε turbulence model. The species transport model with a single-step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in the open literature. The obtained results show that the variation of the divergence angle and backpressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the backpressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also move towards the leading edge of the isolator leading to a rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced backpressures.

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Transient behavior of shock train with and without controlling

Cited by 8 publications

References 41 publications

Correlation Analysis of Separation Shock Oscillation and Wall Pressure Fluctuation in Unstarted Hypersonic Inlet Flow

Correlation Analysis of Separation Shock Oscillation and Wall Pressure Fluctuation in Unstarted Hypersonic Inlet Flow

Numerical Investigation of the Shock Train in a Scramjet with the Effects of Back-Pressure and Divergent Angles

Aerodynamic investigation of the shock train in a scramjet with the effects of backpressure and divergent angles

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