A wall-modeled large-eddy simulation of the OAT15A airfoil complemented by a nacelle of a generic ultra-high bypass ratio turbofan engine is performed at Mach number Ma = 0.73, angle of attack [alpha] = 3.5°, and chord based Reynolds number Rec = 2 * 10^6. The presence of the nacelle geometry leads to noticeable changes of the flow conditions of the airfoil which are characterized by streamline diversion and a shock wave on the upper part of the nacelle. The dynamics of the shock waves is analyzed using dynamic mode decomposition revealing shared fundamental frequencies, which can be reconciled with established buffet models.
Wall-Modeled LES of Buffet under the Influence of Engine Nacelle Flow
2021
8 pages
Miscellaneous
Electronic Resource
English