Aerodynamic performance of nature inspired foils implementing slots

The aim of this research is to present an airfoil with good aerodynamic properties. The airfoil is to be designed such that we can get a better stall and lift efficiency. The boundary layer separation over airfoil is the reason for stall. This stall affects the coefficient of lift for an airfoil by...

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Bibliographic Details
Main Authors: Priyanka, K. Sai, Jeyan, Muruga Lal
Format: Conference Proceeding
Language:English
Subjects:
Aerodynamic coefficients
Airfoils
Angle of attack
Boundary layers
Drag
Flow separation
Mach number
Stalling
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Summary:The aim of this research is to present an airfoil with good aerodynamic properties. The airfoil is to be designed such that we can get a better stall and lift efficiency. The boundary layer separation over airfoil is the reason for stall. This stall affects the coefficient of lift for an airfoil by increasing drag. The boundary layer separation or flow separation is the point where the flow of fluid gets separated from the surface of airfoil. The Slot method can be implemented over the airfoil to reduce the stall and drag resulting in increase of lift. This method is implemented on NACA2418 series airfoil to reduce flow separation. The airfoil is designed using CATIA and analysis of airfoil is done by CFD using ANSYS FLUENT. The parameters like airfoil span is 300mm, chord length is 200mm. The setup is arranged such that the Angle of Attack is about 0 0, 50,100,150, 200 250. Mach number ranging from 0.3 to 0.6. The results from ANSYS shows aerodynamic properties. This provides us the delaying the stall for longer angle of attack and to produce effective lift.
ISSN:0094-243X
1551-7616
DOI:10.1063/5.0196368