Airfoil Lift and Drag Extrapolation with Viterna and Montgomerie Methods

Abstract

In order to compute the performance of a propeller blade using blade element momentum (BEM) method, the two- dimensional airfoil performance of the propeller blade in terms of lift and drag coefficients is necessary. Such data usually can be obtained from model experiment only for limited range of angle of attack (AoA). Therefore, it is necessary to extrapolate the limited experimental data to obtain the data for the whole range of AoA. The present study uses 2 (two) methods which are Viterna and Montgomerie methods in order to extrapolate the performance of an airfoil. The formulas and procedures of both methods are presented and their application are also demonstrated using an airfoil shape of NACA23012. From this study, a relatively good agreement of the airfoil performance in terms of lift and drag coefficients can be found from computation results of the both methods.

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