Abstract
This paper presents the CFD analysis of the 2-Dimensional NACA0012 airfoil carried out for identifying its aerodynamic coefficients (Lift and Drag coefficients), then further implementing morphing technology on the same two-dimensional NACA0012 airfoil, again carrying out CFD analysis to determine its aerodynamic coefficients (Lift coefficient (CL) and Drag coefficient (CD), then comparing the results of both the airfoil shapes particularly to the amount of Lift generated to prove that morphing airfoil produces more amount of Lift when compared to typical airfoil shapes. Using ANSYS Design modeler airfoil geometry was created and morphing shape could be achieved by XFLR5 software further the analysis is carried out using FLUENT 18.1 at subsonic flow. This morphing enables to improve aerodynamic efficiency.
Highlights
Domain SetupThe domain or flow field around the model has the inlet and far field at 15times the chord length i.e. 1000mm from the leading edge of the airfoil, and the outlet is at distance of 25times the chord i.e. 25000mm from the leading edge, as shown in fig
This paper presents the CFD analysis of the 2-Dimensional NACA0012 airfoil carried out for identifying its aerodynamic coefficients (Lift and Drag coefficients), further implementing morphing technology on the same two-dimensional NACA0012 airfoil, again carrying out CFD analysis to determine its aerodynamic coefficients (Lift coefficient (CL) and Drag coefficient (CD), comparing the results of both the airfoil shapes to the amount of Lift generated to prove that morphing airfoil produces more amount of Lift when compared to typical airfoil shapes
In order reduce the consumption of fuel one of the most suitable way is to improve the aircraft performance expanding its flight range
Summary
The domain or flow field around the model has the inlet and far field at 15times the chord length i.e. 1000mm from the leading edge of the airfoil, and the outlet is at distance of 25times the chord i.e. 25000mm from the leading edge, as shown in fig. Meshing of the model is done using ICEM meshing tool. The mesh parameters Eriksson skewness, Aspect ratio, and Determinant are maintained within the acceptable range. The acceptable values for aspect ratio should be less than 30 and greater than 1, values of Eriksson skewness and determinant should be less than 1. As our study concentrated on boundary layer the overall mesh quality doesn’t affect the results so the mesh around the airfoil should be proper
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