Location

Windsor, Ontario

Start Date

25-6-2022 12:00 AM

End Date

25-6-2022 12:00 AM

Description

The amount of solar and background radiation absorbed by birds vary according to their wing shape, pigmentation, porosity, etc. Birds are equipped with unique features to thrive, including attracting opposite sex, regulating body temperatures, and soaring in the sky. The research focuses on solar/sky radiation by examining how NACA0012 airfoil, representing the wing of a bird, performs when its upper surface temperature is higher or lower than the surrounding air. This is realised by performing 2-dimensional simulations in OpenFOAM at a Reynolds Number of 33,000, where Spalart-Allmaras model is used to simulate the flow turbulence. The upper surface of the airfoil is warmed to 330 K and cooled to 270 K at a pressure of 1 atm, an ambient temperature of 300 K, and a Mach number of 0.0725. The results illustrate the airfoil with the cooler top surface exhibits a lower drag and higher lift than its warmer top surface counterpart. A maximum reduction of drag coefficient from 0.065 to 0.061 and increase in lift coefficient from 0.89 to 0.93 at an angle of attack 11° are achieved. In short, tuning the upper surface of NACA0012 airfoil to temperatures lower than the ambient provides better aerodynamic performance.

Included in

Engineering Commons

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Jun 25th, 12:00 AM Jun 25th, 12:00 AM

Bio-inspired study of thermal effects on NACA0012 airfoil at Reynolds Number of 33,000

Windsor, Ontario

The amount of solar and background radiation absorbed by birds vary according to their wing shape, pigmentation, porosity, etc. Birds are equipped with unique features to thrive, including attracting opposite sex, regulating body temperatures, and soaring in the sky. The research focuses on solar/sky radiation by examining how NACA0012 airfoil, representing the wing of a bird, performs when its upper surface temperature is higher or lower than the surrounding air. This is realised by performing 2-dimensional simulations in OpenFOAM at a Reynolds Number of 33,000, where Spalart-Allmaras model is used to simulate the flow turbulence. The upper surface of the airfoil is warmed to 330 K and cooled to 270 K at a pressure of 1 atm, an ambient temperature of 300 K, and a Mach number of 0.0725. The results illustrate the airfoil with the cooler top surface exhibits a lower drag and higher lift than its warmer top surface counterpart. A maximum reduction of drag coefficient from 0.065 to 0.061 and increase in lift coefficient from 0.89 to 0.93 at an angle of attack 11° are achieved. In short, tuning the upper surface of NACA0012 airfoil to temperatures lower than the ambient provides better aerodynamic performance.