Experimental and theoretical study of wings with blunt trailing edges

Ramjee, V.; Tulapurkara, E. G.; Balabaskaran, V.

doi:10.2514/3.45311

Cited by 15 publications

(14 citation statements)

References 6 publications

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“…Experiments show that at same Reynolds number the small values of trailing edge thickness causes an increase in the maximum C L 9,11,12,13 , for higher values of trailing edge thickness the trend is to have a limit in this maximum C L values 12,9 . At a fixed Reynolds number the minimum C D increases as the size of the trailing edge thickness increases 9,12,13 .…”

Section: Andmentioning

confidence: 92%

“…Therefore the initial objective of this research is to determine the level of influence, in the aerodynamic characteristics at low Reynolds numbers [1][2][3][4][5][6] , of these imperfections in the manufacture, and determine whether there may be a value for which it would not be necessary to correct them. Previous studies on simply truncated trailing edge to achieve the required trailing edge thickness 8,11 , or adding thickness to either side of the chamber line 12,13 exhibits increased maximum lift but increased minimum drag also.…”

Section: Introductionmentioning

confidence: 94%

“…10). Early investigations of the short bubble mainly focused on predicting the short bubble burst [9][10][11] . Although the precise prediction of the short bubble burst has not been accomplished, it was revealed that the laminar transition and turbulent flow inside the short bubble play an important role in determining the short bubble burst.…”

Section: Andmentioning

confidence: 99%

See 2 more Smart Citations

Aerodynamic Analysis of Open Trailing Edge Airfoils at Low Reynolds Number

Sant

Ayuso

Meseguer

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Section: Andmentioning

confidence: 92%

Section: Introductionmentioning

confidence: 94%

See 1 more Smart Citation

Aerodynamic Analysis of Open Trailing Edge Airfoils at Low Reynolds Number

Sant

Ayuso

Meseguer

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…For blunt airfoil, Ramjee [8] studied experimentally four different truncations and found that the highest lift coefficient accured at airfoil with 15% of truncation. In this blunt airfoil model, NACA0012 was truncated at 15% of chord length from trailing edge as drawn in the Fig.…”

Section: A Airfoil Designmentioning

confidence: 99%

A Study of Modified Vertical Axis Tidal Turbine to Improve Lift Performance

Arini¹,

Turnock²,

Tan³

2016

IJOEE

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A design of Darrieus vertical axis tidal turbine using modified airfoil was studied numerically in this work. The turbine design was evaluated in 2D CFD model using kω turbulence model, upwind interpolation scheme and simulated using OpenFOAM. The turbine had three blades which were arranged symmetrically. The blades were of NACA 0012 airfoil which had been modified in the trailing edge region to increase its lift performance. The modification was made by truncating the trailing edge at the 15% of chord length from the trailing edge. Single normal and blunt airfoil were modelled and investigated prior to the turbine design evaluation. For generating the mesh, Cstructured grid was employed to the single airfoil model and hybrid mesh to the vertical axis tidal turbine model. From the single airfoil simulations, it was found that blunt NACA0012 had 12% higher lift coefficient than normal airfoil and the pressure coefficient magnitude of blunt vertical axis tidal turbine significantly rise two times from vertical axis tidal turbine using normal NACA0012 airfoil.  Index Terms-vertical axis tidal turbine, Darrieus turbine, truncated Naca0012, blunt airfoil

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“…Futhermore, the increase in pressure drag that comes as a result of a thick trailing-edge will be more noticeable for a thin airfoil. In a similar study performed by Ramjee et al [35], it was noted that the increase in drag associated to thick trailing-edges was mostly apparent at low angles of attack whereas at high angles of attack, the flow separated near the leading-edge, hence the increase in profile drag near the aft portion that arose from the thick trailing-edge had little effect.…”

Section: Flatback Airfoilsmentioning

confidence: 73%

The Multi-Objective Design of Flatback Wind Turbine Airfoils

Miller¹

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With the ever increasing lengths of today's wind turbine rotor blades, there is a need for airfoils which are both aerodynamically, and structurally efficient. In this work, a multi-objective genetic algorithm coupled with XFOIL was developed to design flatback wind turbine airfoils. The effect of the aerodynamic evaluator, specifically lift-to-drag ratio, torque, and torque-to-thrust ratio, on the airfoil shape and performance was examined. Under the specified set of constraints and objectives, notable differences, particularly in the levels of lift and roughness insensitivity, were observed.Further analysis, employing the Taguchi method, was performed to determine how various parameters impact the design outcome. The obtained knowledge was used to design a wind turbine specific airfoil family which has comparable, or superior structural and aerodynamic performance as compared to airfoils found in the literature. A wind tunnel experimental set-up was developed at the Carleton University LowSpeed Wind Tunnel for the 2D testing of airfoils. Good agreement between the results obtained at Carleton University and other publicly available data indicates that the set-up is capable of producing meaningful data. A select airfoil, designed by the current author, was tested at Carleton University and its performance is compared to the numerical predictions of XFOIL. Differences in the stall and post-stall regions of the XFOIL predictions are highlighted, and emphasize the importance of wind tunnel testing in the airfoil design process.iii

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Experimental and theoretical study of wings with blunt trailing edges

Cited by 15 publications

References 6 publications

Aerodynamic Analysis of Open Trailing Edge Airfoils at Low Reynolds Number

Aerodynamic Analysis of Open Trailing Edge Airfoils at Low Reynolds Number

A Study of Modified Vertical Axis Tidal Turbine to Improve Lift Performance

The Multi-Objective Design of Flatback Wind Turbine Airfoils

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