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Review Article Volume 3 Issue 2
Computational analysis of NACA 0010 at moderate to high Reynolds number using 2D panel method
Vasishta Bhargava
GITAM University, India
Received: February 14, 2019 | Published: March 19, 2019
Citation: Bhargava V. Computational analysis of NACA 0010 at moderate to high Reynolds number using 2D panel method. MOJ App Bio Biomech.2019;3(2):48-54. DOI: 10.15406/mojabb.2019.03.00098
Abstract
Wing structures as found in aircrafts and wind turbine blades are built from airfoils. Computational methods are often used to predict the aerodynamic characteristics of airfoils, typically the force and pressure coefficients along its chord length. In the present work, pressure coefficient distribution of NACA 0010 is evaluated using the 2D panel method for incompressible lifting flows at moderate to high Reynolds number, Re-3 x105, 5 x105, 1x106. The analysis was conducted for various AOA (angle of attack), between -40 to 200for the airfoil. The non-dimensional pressure is illustrated for upper and lower surfaces of airfoil between 00 to 200angle of attack at specific chord locations of airfoil. The present results from the 2D panel method are validated using the results from Hess & Smith method and inverse airfoil design method implemented for conformal mapped symmetric Jukouwski airfoil of 10% thickness at 40 angle of attack.
Keywords: airfoil, panel method, pressure coefficient, angle of attack, chord, implemented, powered, incompressible, modern, numerical, techniques, flights,conformal, mapped, dimensional, pressure
©2019 Bhargava. This is an open access article distributed under the terms of the, which permits unrestricted use, distribution, and build upon your work non-commercially.
