Viscous equilibrium analysis of heat transfer on blunted cone at hypersonic flow

Pish, F.; Hassanvand, Amin; Gerdroodbary, M. Barzegar; Noori, Sahar

doi:10.1016/j.csite.2019.100464

Cited by 45 publications

(12 citation statements)

References 48 publications

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“…Heat exchangers devices, chemical catalytic reactors, petroleum reservoirs, and so on, have great significance in science and engineering. Due to this, Pish et al 7 recently conducted analysis of viscous equilibrium on blunted cone at hypersonic flow. Mohanty et al 8 in 2015 numerically investigated heat and mass transfer effects of micropolar fluid.…”

Section: Introductionmentioning

confidence: 99%

Mechanism of Soret‐Dufour, magnetohydrodynamics, heat and mass transfer flow with buoyancy force, and viscous dissipation effects

Ahmed

Falodun

Jimoh³

2020

Heat Trans

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This paper examined the mechanism of both positive and negative effects of Soret‐Dufour with heat and mass transfer processes over an accelerating permeable surface. The partial differential flow equations were simplified using similarity variables, and the resulting equations were solved numerically using the spectral homotopy analysis method (SHAM). The SHAM is used in separating nonlinear equations into linear and nonlinear. The physics of each pertinent flow parameters was used to examine their influence on velocity, temperature, and concentration fields. The effect of Soret‐Dufour was examined separately, and its negative effect was used to determine its influence on velocity, temperature, and concentration fields. The result revealed that positive Soret‐Dufour enhances the boundary layer, whereas negative Soret‐Dufour parameter decreases the boundary layer. The result presented in this paper is in good agreement with existing works in literature.

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Section: Introductionmentioning

confidence: 99%

Mechanism of Soret‐Dufour, magnetohydrodynamics, heat and mass transfer flow with buoyancy force, and viscous dissipation effects

Ahmed

Falodun

Jimoh³

2020

Heat Trans

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“…The strength and interaction of the bow shock produced in front of the spike is important for the thermal load on the main body. Previous works has extensively investigated various characteristic of mechanical spike to achieve optimum geometry of this technique [11][12][13] .…”

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confidence: 99%

Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets

Iranmanesh

Alizadeh

Faraji

et al. 2023

Sci Rep

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Due to sever aerodynamic heating, the protection of forebody of scramjet is crucial for hypersonic flight. In present work, a new cooling system is proposed and investigated for the protection of nose cone at hypersonic flight. Computational fluid dynamic is used for the simulation of the lateral and axial coolant jet released from the spike at high-velocity condition. The primary goal is to find optimum jet location for efficient cooling of nose and spike assembly. Influence of two coolant jets (Carbon dioxide and Helium) on the mechanism of cooling system are fully investigated. For simulation, RANS equations are coupled with species transport equation and SST turbulence model. Two different jet configurations (axial disk positions) are investigated to obtain efficient condition for protection of nose cone at hypersonic flight. Our results indicate that the presence of the spike on the nose cone decreases pressure up to 33% on the main body and the shifts the maximum pressure to higher angles because of the deflection of the air stream. Maximum pressure drops about 50% by injection of the coolant disk jet (C2) at angle of 55 deg.

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“…To resolve this issue, the mechanical spike is mounted at the tip of the nose cone and this reduces the drag force although this combination is a big step for the development of the forebody design 7 , 8 . There is a serious challenge in reducing existing drag and heat protection due to aerodynamic heating 9 – 11 .…”

Section: Introductionmentioning

confidence: 99%

Influence of coolant multi-jets on heat reduction of nose cone with blunt spike at hypersonic flow

Ghanbari

Maddah

Alinejad

2022

Sci Rep

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The importance of the cooling system for the design of the forebody of high-speed vehicles is significant due to severe aerodynamic heating at hypersonic flight. In the present study, injection of multi and single-coolant jets on the thermal performance of forebody design of nose cone with the cut spike is thoroughly investigated at hypersonic flow. A three-dimensional model of the blunt cone is presented for computational investigations of proposed jet and spike configurations. Injection of two coolant gasses (Helium and carbon dioxide) into the cooling system of the nose cone with a blunt spike is investigated. Three locations for both opposing and lateral jets are compared to find the efficient jet location. Our results indicate that a single lateral jet injected from the tip of the spike is more efficient for heat reduction. A comparison of the multiple injection system also shows that the heat reduction of the helium gas is about 15% more than CO2 jets.

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Viscous equilibrium analysis of heat transfer on blunted cone at hypersonic flow

Cited by 45 publications

References 48 publications

Mechanism of Soret‐Dufour, magnetohydrodynamics, heat and mass transfer flow with buoyancy force, and viscous dissipation effects

Mechanism of Soret‐Dufour, magnetohydrodynamics, heat and mass transfer flow with buoyancy force, and viscous dissipation effects

Numerical investigation of compressible flow around nose cone with Multi-row disk and multi coolant jets

Influence of coolant multi-jets on heat reduction of nose cone with blunt spike at hypersonic flow

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