Université de Sherbrooke. Département de Génie mécanique
Abstract
Abstract: A wall-resolved compressible large-eddy simulation and windtunnel experiments are performed on a finite-span supercitical airfoil to investigate the side-edge flow structures and noise sources. The geometry is composed of an isolated supercritical profile (2% camber, 13% thickness) with finite span. The chordwise Reynolds number is 620,000 and the free-stream Mach number is 0.09. The aerodynamic results obtained with a compressible unstructured Large Eddy Simulation solver show the development of turbulent structures from the boundary layer on the airfoil, along with the trajectory of the primary and secondary vorticies. Surface wall shear stress pathlines are compared with experimental oil-flow visualization results yielding good agreement, especially at flow impingement locations. Wall RMS pressure contours highlight the side-edge shear layer and flow impingement of the primary vortex at the pressure side edge to be important noise generation mechanisms. The Ffowcs Williams and Hawkings analogy is used to compute the far-field noise levels. The aeroacoustics simulation results are then compared to the experimental results.Communication présentée lors du congrès international tenu conjointement par Canadian Society for Mechanical Engineering (CSME) et Computational Fluid Dynamics Society of Canada (CFD Canada), à l’Université de Sherbrooke (Québec), du 28 au 31 mai 2023
