Aéroélasticité : aspect numérique

Aeroelasticity: numerical aspect

¹ Dassault Aviation & INRIA
² Dassault Aviation

Abstract

Aerodynamic unsteady phenomena, such as flutter, are modelized using robust conception tools. Although crucial for aircraft design, these Iow design tools are not accurate in the transonic domain. The usual approach (see [1] and [2]) relies on linear potential methods, calibrated withflight test measurements, wind tunnel experiments and sophisticated CFD codes simulalions. Large improvements in both numerical methods and computers allow high levels of modelization (Navier-Stokes equations, ...). At the present time, we can consider computations which were formerly unreachable (see for exmnple [11] and [71]. Focusing on accurate methods, we present in this paper results obtained with several modelizations of unsteady phenomena, each of them corresponding to precise needs (flight manoeuvre, small displacements of control surfaces, parafoil, ...). Finally, an alternate technique is currently being developped, halfway between classical tools and the most detailed modelizations, and begins being used in industrial context. The crucial point of this technique is to solve the linearized Euler (or Navier-Stokes) equations [3]). Results obtained using a linearized Euler solver (based on a discrete approach) are presented.