Computational Fluid Dynamics of Airfoil Sections

Abstract

Airfoil plays an important role in any aircraft and chooses whether the lift power is adequate to adjust the heaviness of the body or not and the amount of drag power is being connected on the body. The main objective of this investigation is to analyze the flow behavior around the airfoil body and to calculate the performance coefficients at higher Reynolds Number (1.04×105) and angle of attack varying from -5 degrees to 20 degrees. The section-lift and drag coefficient for airfoils are obtained by analyzing the measured pressure distribution on the airfoil surface. The simulations were computed in the software ANSYS 15.0 FLUENT. FLUENT software screens the surface weight and gives a visual presentation of the element changes connected with shifting approach. By plotting the bend L/D, yields the most proficient aero foil approach. Lift increments as the approach ascends from -5 to 20 degrees and at a specific point, most extreme lift is produced. On the off chance that the approach is expanded any further, drag turns into the overwhelming component and the area enters the stall mode. A simple approach called PANEL method is used to validate the results obtained from FLUENT software. This approach can be further used as function in inverse design of airfoil sections for desired pressure distributions.