EFFECT OF DYNAMIC ROLLING OSCILLATIONS ON TWIN-TAIL BUFFET RESPONSE

Abstract

The effect of dynamic rolling oscillations of delta-wing/twin-tail configuration model on twin-tail buffet response is investigated. The configuration model is statically pitched at a 30° angle of attack and then forced to oscillate in roll around the symmetry axis at a constant amplitude of 4° and reduced frequency of π and 2π . This multidisciplinary problem is solved using three sets of equations on a dynamic multi-block grid structure. The first set is the unsteady, full Navier–Stokes equations, the second set is the aeroelastic equations for coupled bending and torsion vibrations of the tails, and the third set is the grid-displacement equations. The results conclusively showed that the rolling oscillations of the configuration have led to higher loads, higher deflections, and higher excitation peaks than those of the stationary configuration. Moreover, increasing the reduced frequency has led to higher loads and excitation peaks and lower bending and torsion deflections and acceleration. The unsteady aerodynamic loads have never reached complete periodicity due to the irregular vibrations of the left and right tails.