Aerodynamic behavior and flow visualization on canonical NACA airfoils at low Reynolds number

Durgesh, Vibhav; Johari, Hamid; Garcia, Elifalet

doi:10.1007/s12650-023-00910-w

Cited by 2 publications

(3 citation statements)

References 32 publications

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“…NACA airfoils have been widely studied, mainly in the atmospheric flight range (10 5 -10 7 ). For extremely low Reynolds numbers, they have been studied for use in drones and for use in fixed-wing and rotary-wing vehicles on Mars, as we have seen in literature references [12][13][14][15][16]. The authors have been developing experimental studies with a water channel with NACA airfoils such as 0006, 0010, 0012, 0016, 0018, 0024, and 0032, among others.…”

Section: • Particle Image Velocity In Airmentioning

confidence: 99%

“…Low Reynolds numbers have gained importance in recent years, due to new research paths and recent literature, as cited in [10][11][12]. One of the primary motivations for studying low Reynolds numbers is their potential use in MAVs (micro air vehicles) in the Martian atmosphere [12][13][14][15][16]. In addition, other applications have been proposed, such as reconnaissance in hostile territories or missions in which human life would be at risk, as mentioned in [17,18].…”

Section: Introductionmentioning

confidence: 99%

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Exploring the Effectiveness of Visualization Techniques for NACA Symmetric Airfoils at Extremely Low Reynolds Numbers

Rodríguez-Sevillano,

Casati-Calzada,

Bardera-Mora

et al. 2023

Fluids

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This article aims to highlight the importance of utilizing flow visualization techniques in the preliminary analysis of streamlined and bluff bodies, especially the potential use of visualization with ink in a water channel as a tool for a preliminary approach during fluid mechanics analysis. According to this, the study compares the results obtained using a classical flow visualization technique, ink injection in water, with those obtained through the employment of a laser-based measurement and visualization technique, called PIV, in a low-speed wind tunnel. The article briefly presents both techniques and highlights the importance of flow visualization in the analysis of aerodynamic bodies. This study focuses on flow over NACA airfoils at extremely low Reynolds numbers, which is of great interest for application in extraterrestrial atmospheres, such as on Mars. After obtaining images of the flow streamlines over the NACA 0018 airfoil, the results of both techniques were compared. The results indicated that there was good agreement between the visualization with the water channel and the PIV results, suggesting that the results obtained in the water channel represented a scientifically valid approximation and an essential complement to computational models that require experimental validation.

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Section: • Particle Image Velocity In Airmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Exploring the Effectiveness of Visualization Techniques for NACA Symmetric Airfoils at Extremely Low Reynolds Numbers

Rodríguez-Sevillano,

Casati-Calzada,

Bardera-Mora

et al. 2023

Fluids

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“…They obtained some factors that affect the aerodynamic performance of the NACA0015 airfoil. In addition, other studies [23][24][25][26][27][28][29][30][31][32][33][34][35][36][37][38][39] have focused on the wing winding problem, and important conclusions were obtained.…”

Section: Introductionmentioning

confidence: 99%

Implementation of a PAFV turbulence model for airfoil flow simulation on OpenFOAM

Yan,

Sun,

Sun

et al. 2024

Phys. Scr.

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To further develop a more effective turbulence model and to improve the calculation accuracy of the flow around airfoil, a new PAFV turbulence model has here been constructed by using a deformation rate tensor and the grouping of an average fluctuation velocity. To evaluate the applicability of the PAFV turbulence model, the numerical calculations of flow around the airfoil have here been implemented, which was based on the OpenFOAM calculation platform. On the basis of grid independence research, the model was used to calculate the low-speed flow-around problem for the plano-convex airfoil NACA4412 and the symmetric airfoil NACA0012. It was also compared with the S-A (Spalart-Allmaras) and SST (Shear Stress Transport) k-ω turbulence models. Firstly, the maximum lift angle-of-attack case of the NACA4412 airfoil was calculated. Thereafter, numerical calculations were performed for the flow around the airfoil in the multi-angle-of-attack case of NACA0012 airfoil. The results showed that the NACA4412 airfoil had an obviously separated vortex at the trailing edge of the airfoil at the maximum lift angle of attack. Also, there was a certain velocity loss downstream of the trailing edge, as was calculated by all three models. However, the results of the PAFV turbulence model were found to be better than those of the S-A and SST turbulence models. The three turbulence models showed comparable accuracies for the calculations of the surface pressure coefficients of the NACA0012 airfoil. However, the S-A and SST k-ω turbulence models were slightly better for the calculations of the mean velocity profiles of the NACA0012 airfoil. Also, the PAFV turbulence model was more accurate for the calculations of the lift and drag coefficients. In conclusion, the PAFV model can make effective predictions for the airfoil low-speed flow around the problem at hand, which in turn preliminarily verifies the applicability of this turbulence model for the low-speed flow around airfoil problems.

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Aerodynamic behavior and flow visualization on canonical NACA airfoils at low Reynolds number

Cited by 2 publications

References 32 publications

Exploring the Effectiveness of Visualization Techniques for NACA Symmetric Airfoils at Extremely Low Reynolds Numbers

Exploring the Effectiveness of Visualization Techniques for NACA Symmetric Airfoils at Extremely Low Reynolds Numbers

Implementation of a PAFV turbulence model for airfoil flow simulation on OpenFOAM

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