Abstract:
NACA 4415 is the most common four-digit unsymmetrical aerodynamic shape.
There are various applications of this airfoil in our day-to-day life and the
aerodynamic sector, mostly in the design of fighter aircraft. The flow characteristics
and heat transfer characteristics of the NACA 4415 airfoil are investigated by flow
simulation and heat transfer using the computational method with the help of CFD
in Ansys workbench and experimental analysis as the airfoil approaches the upper
surface of the wind tunnel. The experiments were performed at Reynold’s Number
of 2.5* 105
and different height ratios with various angles of attack. The specific
Reynold’s Number was chosen to ensure that the flow generated is of turbulent type.
The results that were obtained from the experiment are shown in terms of pressure
coefficient, drag coefficient, and Nusselt’s Number for the different height ratios and
different angle of attack. This work is one part of the extensive and general
investigation that is being carried out. The results of the experiment are found in the
above terms as the height ratio decreases and the negative pressure coefficient
decreases. In the case of the heat transfer computation, we have seen that Nusselt’s
number decreases as the decrease of height ratio.
