UGC Approved Journal no 63975(19)

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Published in:

Volume 5 Issue 6
June-2018
eISSN: 2349-5162

UGC and ISSN approved 7.95 impact factor UGC Approved Journal no 63975

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Published Paper ID:
JETIRC006059


Registration ID:
183637

Page Number

331-338

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Title

DESIGN OPTIMIZATION OF AERODYNAMIC PASSIVE FLOW CONTROL ON NACA 0012 AIRFOIL USING VORTEX GENERATORS

Abstract

Flow separation is a major challenge in aerodynamics. It adversely affects the performance of aircraft wings, wind turbine blades and compressor blades. It is also seen over the rear trunk of an automobile and in internal flows. A direct consequence of flow separation over an airfoil is reduction in lift and increase in drag, two aspects that adversely affect the aerodynamic performance of the airfoil. It also causes excessive vibration and loss of control. The underlying cause for flow separation is the lack of energy within the boundary layer to withstand adverse pressure gradients downstream of the airfoil. Vortex generator is a simple aerodynamic device that projects from the top surface of the airfoil. It forms a stream wise vortex that transfers high momentum fluid from the free stream to the boundary layer and low momentum fluid from the boundary layer to the free stream air. Thus the boundary layer is energized to withstand the adverse pressure gradients, hence preventing flow separation. This numerical study focuses on enhancing the lift coefficient of NACA0012 airfoil, by suppressing flow separation using passive rectangular vane type vortex generator. The effect of various vortex generator parameters such as spacing between the vortex generators (z), height of the device (h), local angle of incidence (β) and position of the device from the separation line (∆XVG), on the lift and drag coefficients of the airfoil were studied. Based on which optimum parameters were identified. The optimum configuration is at β =23ᵒ, h/C=0.004, z/C =0.025, ΔXVG /C=.020 with CL=1.0723 and CD=0.1350. The lift coefficient has increased 43.36% from the baseline case and the drag coefficient has decreased by 41.54%.

Key Words

Flow separation, adverse pressure gradients, boundary layer, vortex generators

Cite This Article

"DESIGN OPTIMIZATION OF AERODYNAMIC PASSIVE FLOW CONTROL ON NACA 0012 AIRFOIL USING VORTEX GENERATORS", International Journal of Emerging Technologies and Innovative Research (www.jetir.org), ISSN:2349-5162, Vol.5, Issue 6, page no.331-338, June-2018, Available :http://www.jetir.org/papers/JETIRC006059.pdf

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2349-5162 | Impact Factor 7.95 Calculate by Google Scholar

An International Scholarly Open Access Journal, Peer-Reviewed, Refereed Journal Impact Factor 7.95 Calculate by Google Scholar and Semantic Scholar | AI-Powered Research Tool, Multidisciplinary, Monthly, Multilanguage Journal Indexing in All Major Database & Metadata, Citation Generator

Cite This Article

"DESIGN OPTIMIZATION OF AERODYNAMIC PASSIVE FLOW CONTROL ON NACA 0012 AIRFOIL USING VORTEX GENERATORS", International Journal of Emerging Technologies and Innovative Research (www.jetir.org | UGC and issn Approved), ISSN:2349-5162, Vol.5, Issue 6, page no. pp331-338, June-2018, Available at : http://www.jetir.org/papers/JETIRC006059.pdf

Publication Details

Published Paper ID: JETIRC006059
Registration ID: 183637
Published In: Volume 5 | Issue 6 | Year June-2018
DOI (Digital Object Identifier):
Page No: 331-338
Country: -, -, -- .
Area: Engineering
ISSN Number: 2349-5162
Publisher: IJ Publication


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