Mass-averaging pseudo-shock model in a straight flow passage

Matsuo, Kimiko; Miyazato, Yoshiaki; Kim, H D

doi:10.1243/0954410991533089

Cited by 19 publications

(9 citation statements)

References 17 publications

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“…Ikui et al(1974) proposed the diffusion model to predict the length of the pseudo shock wave, which refines the shockless model developed by Tamaki et al(Tamaki et al 1970;Tamaki et al 1971). Likewise, the mass averaging pseudo-shock model for a constant area duct with a fully turbulent boundary layer is proposed by Matsuo et al (1999b). This model predicts the downstream flow properties of the pseudo-shock solely from the upstream mass averaged values.…”

Section: Introductionmentioning

confidence: 94%

Numerical Study on Shock Train Characteristics in Divergent Channels

Ram¹,

Kim²,

Kim³

2020

JAFM

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In any supersonic intake, the flow decelerates from supersonic to subsonic speed through a constant or divergent channel "isolator" by a series of bifurcated compression shock waves referred to as a shock train. It is important to understand the characteristics of the shock train which occur inside the isolator to improve the performance of scramjet engines. In the present work, numerical simulations were carried out to investigate the characteristics of the shock train occurring in the divergent channels using coupled implicit Reynolds Averaged Navier-Stokes (RANS) equations along with the two-equation k-w SST turbulence model. Results show that the downstream pressure variation causes the shock train length to decrease and the shock structure phenomenon varies from Mach reflection to Regular reflection. The variation of the inlet Mach number has less influence on the shock train length and the location of the shock train is determined by the area ratio. In comparison with the constant area duct, the shock train structure phenomena varies from Mach reflection to regular reflection in the divergent channel. Also, the increase in divergent angle raises the total pressure loss.

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Section: Introductionmentioning

confidence: 94%

Numerical Study on Shock Train Characteristics in Divergent Channels

Ram¹,

Kim²,

Kim³

2020

JAFM

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“…/ p:uldA = / p2u2dA (11) /(p: + p:u~)dA = /(p2 + p2u~)dA (12) /(CpT: + ~ + q)p:u:dA U 2 =/(CpT2+ 2)p2u2dA (13) where Cp is specific heat at constant pressure, and q amount of heat per unit mass supplied into the control volume. The equation of state for a perfect gas with ratio of specific heats V = 1.4 is given by…”

Section: Control Volume Analysismentioning

confidence: 99%

“…where n is the power law index which is related to the boundary layer Reynolds number [ 13] and u = ul~ for 5: ,< y < D/2.…”

Section: Control Volume Analysismentioning

confidence: 99%

One-dimensional analysis of thermal choking in case of heat addition in ducts

et al. 2000

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The thermal choking phenomenon is of great importance in an inlet isolator in dual-mode ram jet/scramjet combustor. In some cases the choked flow creates a pseudo-shock wave including a shock train in it at the engine inlet and causes large amounts of drag and radically reduces the performance of the engine at high flight Mach numbers. The present paper describes a one-dimensionM flow model taking account of the upstream boundary-layer as well as heat addition by using a mass-weighted averaging technique. The simple relationships for the flow field in a constant area duct in which the effect of the upstream boundary-layer is considered but the effect of the wall friction in the duct can be neglected are presented. The results of the calculation such as the maximum heat addition when the thermal choking occurs, the downstream Mach number and the static pressure ratio are presented and examined in detail.

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“…6 The aim of the PSC is to mitigate the risk of unstart through monitoring the isolator pressure signals. Many researchers have studied the steady and unsteady characteristics of the shock train, 7–13 which lay a solid foundation for the shock train leading edge (STLE) detection.…”

Section: Introductionmentioning

confidence: 99%

A method for shock train leading edge detection based on differential pressure

Xiong

Wang

Fan

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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In order to make the shock train leading edge detection method more possible for operational application, a new detection method based on differential pressure signals is introduced in this paper. Firstly, three previous detection methods, including the pressure ratio method, the pressure increase method, and the standard deviation method, have been examined whether they are also applicable for shock train moving at different speeds. Accordingly, three experimental cases of back-pressure changing at different rates were conducted in this paper. The results show that the pressure ratio and the pressure increase method both have acceptable detection accuracy for shock train moving rapidly and slowly, and the standard deviation method is not applicable for rapid shock train movement due to its running time window. Considering the operational application, the differential pressure method is raised and tested in this paper. This detection method has sufficient temporal resolution for rapidly and slowly shock train moving, and can make a real-time detection. In the end, the improvements brought by the differential pressure method have been discussed.

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Mass-averaging pseudo-shock model in a straight flow passage

Cited by 19 publications

References 17 publications

Numerical Study on Shock Train Characteristics in Divergent Channels

Numerical Study on Shock Train Characteristics in Divergent Channels

One-dimensional analysis of thermal choking in case of heat addition in ducts

A method for shock train leading edge detection based on differential pressure

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