Design load predictions on a fighter-like aircraft wing

Abstract

Numerical solutions for a transonic design condition have been obtained for a fighter-like aircraft wing geometry using Euler and Navier-Stokes equations. Both rigid and flexible wings are considered. Effects of viscosity and static aeroelasticity on the component loads such as shear, bending moment, and torsion, as well as hinge moments on the flaps and ailerons, are predicted. The flexible wing solutions are obtained by coupling the flow solvers with a simple NASTRAN model. Effects of fuselage and horizontal tail have also been obtained for the rigid wing case using Euler equations. The computed results are compared to available flight test data. It is found that the static aeroelasticity has only a minor role, whereas the effect of viscosity is very pronounced. Comparison with the flight test data is found to be best when viscous effects are included.