Triglobal infinite-wing shock-buffet study

This article uses triglobal stability analysis to address the question of shock-buffet unsteadiness, and associated modal dominance, on infinite wings at high Reynolds number, expanding upon recent biglobal work, aspiring elucidate flow phenomenon's origin characteristics. Infinite are modelled by extruding an aerofoil finite aspect ratios imposing a periodic boundary condition without assumptions spanwise homogeneity. Two distinct steady base flows, uniform non-uniform, analysed herein straight swept wings. Stability straight-wing identifies both oscillatory mode, linked chordwise shock motion synchronised with pulsation its downstream shear layer, several monotone (non-oscillatory), spatially shock-distortion modes. Those modes become outboard travelling wing their respective frequencies phase speeds correlated sweep angle. In limiting case very small wavenumbers approaching zero, effect creates branches inboard Overall, results for such quasi-three-dimensional flows agree previous studies. On contrary, cellular patterns form in proper three-dimensional wings, we present first study equilibrium solution governing equations. Spanwise-irregular found be sensitive chosen ratio. Nonlinear time-marching simulations reveal evolution events confirm insights gained through dominant from routine analysis.