Cargas Aerodinámicas sobre Superficies Sustentadoras en Flujo Subsónico (Casos Estacionario y no Estacionario)

Abstract

A method with its correspondent computer program for calculating the unsteady aerodynamic loads harmonically oscillating wings in subsonic flow, has been developed. Because of its simplicity and versatility it can easily be applied to complex planform wings, even if they have control surfacdes. For this method to be applied, the wing has to be divided on a certain numbewr of surface panel elements on each of which the 1/4-3/4 chord rule is adopted. That is, a concentrated aerodynamic load at the 1/4 panel chord point is computer with the tangent flow condition imposed at the 3/4 chord point. Numerical calulations were carried out for several wing sieometries. The results obtained are presented and compared with other analysis and experiments.