res = xf.find_pressure_coefficients(airfoil='naca' + airfoil, alpha=AoA, NACA=True, ) x_foil_cl = xf.find_coefficients(airfoil='naca' + airfoil, alpha=AoA, NACA=True ...
ABSTRACT: This paper presents an implementation and posterior analysis of the convergence of the panel method. The implemented panel method is based on vortex lines and an unsteady wake on a flat ...
Abstract: Two induced drag analysis techniques, Vortex Lattice Method (VLM) and panel method are renowned for inviscid aerodynamic computations and are widely used in the aerospace industry and ...
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