Numerical Study of Heat Transfer Around the Small Scale Airfoil Using Various Turbulence Models

Bekka, Nadir; Bessaïh, Rachid; Sellam, Mohamed; Chpoun, A.

doi:10.1080/10407780903508005

Cited by 14 publications

(7 citation statements)

References 31 publications

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“…Lastly, we investigate the impact of the thermal boundary conditions on the sound propagation; it will be shown that the wall temperature increment can reduces the lift pulsation and increase the drag generated the by Karman vortex street that is shed behind blu↵ bodies. Similar results were already found for the lift and drag modification on low Reynolds number operating airfoils [8][9][10]. In this context lift reduction is a very important element since it can lead to an aeroacoustic perturbation decay and in a modification of the sound directivity.…”

Section: Introductionsupporting

confidence: 84%

“…Because of the alternation of vortices detachment and their location downstream to the cylinder, the dipole axis is not aligned with the undisturbed flow direction. As already noted in [8][9][10], the wall temperature increase produces a drag force growth and a instantenuos lift force reduction. It is recognized that this evidence is related to a thermal e↵ect on the pressure and to a local dynamic viscosity modification.…”

Section: Thermal Effects On Aeolian Tonessupporting

confidence: 60%

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A low—storage Runge—Kutta OpenFOAM solver for compressible low—Mach number flows: aeroacoustic and thermo—fluid dynamic applications

et al. 2019

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A solver for compressible Navier–Stokes equations is presented in this paper. Low-storage RungeKutta schemes were adopted for time integration; on the other hand the finite volume approach available within OpenFOAM library has been adopted for space discretization. Kurganov-Noelle-Petrova approach was used for convective terms, while central schemes for diffusive ones. The aforementioned techniques were selected and tested in order to allow the possibility of solving a broad range of physical phenomena with particular emphasis to aeroacoustic and thermo-fluid dynamic problems. Indeed, that standard OpenFOAM solution techniques produce an unacceptable dissipation for acoustic phenomena computations. Non–reflective boundary treatment was also considered to avoid spurious numerical reflections. The reliability and the robustness of the solver is proved by computing several benchmarks. Lastly, the impact of the thermal boundary conditions on the sound propagation was analyzed.

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Section: Introductionsupporting

confidence: 84%

Section: Thermal Effects On Aeolian Tonessupporting

confidence: 60%

A low—storage Runge—Kutta OpenFOAM solver for compressible low—Mach number flows: aeroacoustic and thermo—fluid dynamic applications

et al. 2019

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“…By cooling the extrados and heating the intrados, Kim et al (2003) [8] achieved to enhance lift and reduce drag, especially significant for small-scale airfoils. The same results were obtained by Bekka et al (2009) [9] using a numerical computation of the flow around microscale wing for MAV with and without thermal effect. A more specific study of influence of heat transfer on the aerodynamic performance of a plunging and pitching NACA0012 airfoil at low Reynolds numbers can be found in Hinz et al (2013) [10].…”

Section: Introductionsupporting

confidence: 66%

Numerical Study of the Aerodynamic Performance of Naca 0012 in the Presence of an Unsteady Heat Source

Soto¹,

Porfiriev

2016

Collection of Selected Papers of the II International Conference on Information Technology and Nanotechnology

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Abstract. The objective of this paper is to study the effect of an unsteady moving heat source on the aerodynamic performance of an NACA 0012 airfoil section, with particular focus on the lift and drag coefficients. The compressible Navier-Stokes equations are solved using a finite volume method as well as Spalart-Allmaras Model for turbulence simulation. The heat source periodically moves over the lower surface of the airfoil in the downstream direction. The numerical results show how the drag and lift coefficient strongly depend upon the velocity of the source. For a constant source power, a progressive improvement in the mean values of lift and drag coefficients is observed as velocity increases.Keywords: aerodynamic performance, heat source, lift coefficient, drag coefficient, computational fluid dynamics. IntroductionOptimizing aerodynamic performance and increasing the reliability of flying machines has led scientists to find new methods that simultaneously provide increase in the lift and reduce drag. One of those approaches has been using procedures based on heat transfer effects. Over the last decades, several numerical and analytical methods to study heat effects have been developed. Generally, the effect is studied by imposing steady temperature differences between the airfoil surface and the freestream. For example, Norton et al. (1973) [1] studied the case of NACA 0012 heated at different ratios and considering both laminar and turbulent flows over the surface. Their results showed a destabilization of the boundary layer, earlier transition and separation for temperature ratio bigger than unity. The paper showed a reduction in the value of Cl max and an increase in drag as the airfoil was heated.

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“…The leading or trailing edge separation events increase drag and reduce lift [2]. In other recent studies [3], airfoils improved aerodynamic performance under surface heat treatment has been investigated. Due to the reduced size of the MAVs, compared to the older models, heat transfer effects are significant.…”

Section: Introductionmentioning

confidence: 99%

Untitled

2022

IJEM

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In this investigation, finite difference lattice Boltzmann method (FD_LBM) is developed to solve heat transfer effect behavior on the symmetrical and unsymmetrical airfoils with plunge oscillations. In this simulation, the equations of motion and energy are executed using LBM and FD simultaneously. The LB method is integrated with ghost flow for predicted curve boundary. The ghost flow method is a Cartesian-based method that, in addition to being practical and straightforward, retains many advantageous features of structured meshes, can be used for complex geometries, and has a high degree of flexibility. In other words, when the body oscillates, it is important to determine its position caused by the change in the mesh structure at any time. While the ghost method detects the object's position well, the new technique can capture the details of flow more accurately and stably than the other methods. Combining the ghost method with LBM provides a new technique that can investigate thermal behavior's effect on the airfoil with greater accuracy and stability. This combination of modern methods with high accuracy and stability in complex geometries has not been studied. The results are compared with the literature and show that this method has better convergence in different Reynolds and temperatures with changes at boundary conditions in the airfoil.

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Numerical Study of Heat Transfer Around the Small Scale Airfoil Using Various Turbulence Models

Cited by 14 publications

References 31 publications

A low—storage Runge—Kutta OpenFOAM solver for compressible low—Mach number flows: aeroacoustic and thermo—fluid dynamic applications

A low—storage Runge—Kutta OpenFOAM solver for compressible low—Mach number flows: aeroacoustic and thermo—fluid dynamic applications

Numerical Study of the Aerodynamic Performance of Naca 0012 in the Presence of an Unsteady Heat Source

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