Study of Turbulence-Radiation Interaction in Hypersonic Turbulent Boundary Layers

Duan, Lian; Martı́n, M. Pino; Feldick, Andrew; Modest, Michael F.; Levin, Deborah A.

doi:10.2514/1.j051247

Cited by 5 publications

(7 citation statements)

References 34 publications

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“…Close to the separation area (x = 0.8), a significant cooling effect of the thermal boundary layer is observed, which is mainly due to the influence of thermal radiation. This phenomenon was also observed in previous numerical and theoretical studies regarding compressible and turbulent flows [19,20,61,62].…”

Section: Resultssupporting

confidence: 84%

“…In Section 3, a short description of HAM is given together with its specific application for the physical problem studied in this paper. Finally, in Section 4, a thorough discussion of the obtained results is given with respect not only to the effect of a pressure gradient and radiation but also to numerical results concerning similar but not identical physical problems [3,5,6,19,20,61,62]. The presented results are novel, especially concerning the radiation effect on the boundary layer flow under the effect of a pressure gradient.…”

Section: Introductionmentioning

confidence: 94%

“…In [18], a computational model was presented for convective and radiative heat transfer of very high temperature gas cooled and gaseous core reactors, with results that are in very good agreement with experimentally based correlations. In [19,20], the interaction of flow with radiation was studied in hypersonic boundary layer flows. In [21,22], a comprehensive numerical analysis of heat transfer in a rectangular enclosure was performed, and several effects on the fluid flow and heat transfer have been extensively studied, such as the effects of the Rayleigh number, thermal conductivity ratio, as well as internal surface emissivity.…”

Section: Introductionmentioning

confidence: 99%

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Solving the Nonlinear Boundary Layer Flow Equations with Pressure Gradient and Radiation

et al. 2020

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The physical problem under consideration is the boundary layer problem of an incompressible, laminar flow, taking place over a flat plate in the presence of a pressure gradient and radiation. For the mathematical formulation of the problem, the partial differential equations of continuity, energy, and momentum are taken into consideration with the boundary layer simplifications. Using the dimensionless Falkner–Skan transformation, a nonlinear, nonhomogeneous, coupled system of partial differential equations (PDEs) is obtained, which is solved via the homotopy analysis method. The obtained analytical solution describes radiation and pressure gradient effects on the boundary layer flow. These analytical results reveal that the adverse or favorable pressure gradient influences the dimensionless velocity and the dimensionless temperature of the boundary layer. An adverse pressure gradient causes significant changes on the dimensionless wall shear parameter and the dimensionless wall heat-transfer parameter. Thermal radiation influences the thermal boundary layer. The analytical results are in very good agreement with the corresponding numerical ones obtained using a modification of the Keller’s-box method.

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Section: Resultssupporting

confidence: 84%

Section: Introductionmentioning

confidence: 94%

Section: Introductionmentioning

confidence: 99%

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Solving the Nonlinear Boundary Layer Flow Equations with Pressure Gradient and Radiation

et al. 2020

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“…Their results are compared with experimentally based correlations, showing a good agreement. Duan et al have studied the emission turbulence-radiation interaction in hypersonic boundary layer flows [24] [25]. In this study, when emission is coupled to the flow, the temperature is drastically decreased in the turbulent layer.…”

Section: Xenosmentioning

confidence: 95%

Thermal Radiation Effect on the MHD Turbulent Compressible Boundary Layer Flow with Adverse Pressure Gradient, Heat Transfer and Local Suction

Xenos¹

2017

OJFD

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The combined effect of magnetic field, thermal radiation and local suction on the steady turbulent compressible boundary layer flow with adverse pressure gradient is numerically studied. The magnetic field is constant and applied transversely to the direction of the flow. The fluid is subjected to a localized suction and is considered as a radiative optically thin gray fluid. The Reynolds Averaged Boundary Layer (RABL) equations with appropriate boundary conditions are transformed using the compressible Falkner Skan transformation. The nonlinear and coupled system of partial differential equations (PDEs) is solved using the Keller box method. For the eddy-kinematic viscosity the Baldwin Lomax turbulent model and for the turbulent Prandtl number the extended Kays Crawford model are used. The numerical results show that the flow field can be controlled by the combined effect of the applied magnetic field, thermal radiation, and localized suction, moving the separation point, s x , downstream towards the plate's end, and increasing total drag, D . The combined effect of thermal radiation and magnetic field has a cooling effect on the fluid at the wall vicinity. The combined effect has a greater influence in the case of high free-stream temperature.

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“…This computational model considers the turbulent compressible flow under the radiation effect in a large temperature range [7]. The emission turbulence-radiation interaction in hypersonic BLs was studied by Duan et al [8] [9].…”

Section: Introductionmentioning

confidence: 99%

Mathematical Formulation of Bubble Formation after Compressible Boundary Layer Separation: Preliminary Numerical Results

Xenos¹

2022

OJFD

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Laminar boundary layer (BL), under adverse pressure gradient, can separate. The separated shear layer reattaches to form a laminar separation bubble. Such bubbles are usually observed on gas turbine blades, on low Reynolds number wings and close to the leading edges of airfoils. Presence of bubbles has a weakening effect on the performance of a fluid device. The understanding of the prevailing mechanism of the separation bubble and ways to control it are essential for the efficient design of these devices. This is due to the significance of drag reduction in these various aerodynamic devices, such as gas turbines, re-entry space vehicles and airfoils. This study introduces a two-dimensional mathematical formulation of bubble formation after flow separation. The laminar BL equations with appropriate boundary conditions are dimensionalized using the Falkner-Skan transformation. Additionally, using the Keller-box method, the nonlinear system of partial differential equations (PDEs) is numerically solved. This study presents preliminary numerical results of bubble formation in low Mach numbers. These results reveal that after separation, a laminar bubble is formed in all studied cases, for Mach numbers, M = 0.2, 0.33 and 1.0. The flow after separation reverses close to the wall and finally reattaches downstream, in a new location. As the Mach number increases, this effect is more intense. After reattachment, the BL is again established in a lower energy level and the velocity field is substantially reduced, for all cases.

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Study of Turbulence-Radiation Interaction in Hypersonic Turbulent Boundary Layers

Cited by 5 publications

References 34 publications

Solving the Nonlinear Boundary Layer Flow Equations with Pressure Gradient and Radiation

Solving the Nonlinear Boundary Layer Flow Equations with Pressure Gradient and Radiation

Thermal Radiation Effect on the MHD Turbulent Compressible Boundary Layer Flow with Adverse Pressure Gradient, Heat Transfer and Local Suction

Mathematical Formulation of Bubble Formation after Compressible Boundary Layer Separation: Preliminary Numerical Results

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