Airfoil angle incidence effect on the shear stress evaluation
DOI:
https://doi.org/10.38152/bjtv7n4-017Keywords:
shear stress, shear force, static moment, moment of inertia, product of inertia, cubic spline interpolation, airfoils, coefficient of τmax, angle of incidence, coefficient of comparison of τmax between two airfoils, coefficient of comparison of areas between two airfoilsAbstract
The aim of this work is to develop a new numerical calculation program to determine the effect of rotation of the airfoil surface on the calculation of the maximum shear stress value due to the effect of the two shear forces from the aerodynamic forces. The airfoil is generally given by tabulated values, whose cubic spline interpolation is used to determine an analytical shape for its extrados and intrados. The shear stress formula is based on the calculation of the static moments of the upper part in relation to the central horizontal and vertical axes, and also on the evaluation of its central moments and product of inertia. Calculation of the value of the maximum shear stress is necessary for each airfoil and for each incidence angle. A maximum shear stress coefficient µ is calculated as a normalized maximum stress by the airfoil chord for each incidence angle. A comparison of the maximum stress of an airfoil compared to that of NACA 0012 reference is made to see the effectiveness of existing airfoils in aerospace construction against the shear phenomenon compared to a reference airfoil. In this context, two new coefficients λ and ψ named respectively by comparison coefficient of the maximum stress and comparison coefficient of the sectional area of an airfoil compared to those of NACA 0012 are evaluated. The application is made for 5 airfoils NACA 0012, RAE 100, EPPLER 520, BOEING 737, B-29.
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