Static Aeroelastic Analysis of a Complex Wing-Body Configuration using CFD

摘要

The growing requirements of extended range and maneuverability of missile configurations lead to the incorporation of thin aerodynamic surfaces (wings) with high aspect ratio. These kinds of wings tend to be flexible. As a result, large deformation of the structure can occur at some flight conditions. This elasticity is not negligible and may affect the static and dynamic aerodynamic characteristics of the configuration. A closely-coupled aeroelastic analysis is applied for a complex realistic configuration at nonlinear flow regimes. This approach suggests a numerical simulation in which the flow computations and elastic deformations are embedded within one CFD code, and performed within a single run. The CFD code used in our research is EZNSS (Elastic Zonal Navier-Stokes Solver) of the Israeli CFD Center (ISCFDC). The method is tested on a specific wing with an aspect ratio of 6. The significant aeroelastic deformations, such as wing bending and torsion, are obtained. Their influence on aerodynamic characteristics of a total configuration is discussed. The dependence of the aerodynamic coefficients on the dynamic pressure is also shown. In addition, some comparisons with rigid results and wind-tunnel tests are presented. This work shows that aeroelastic analysis overcomes the frames of the academic discipline and can serve as an effective tool for aerodynamic modeling, even for complex configurations and nonlinear flow conditions.