Aerodynamic and Aeroacoustic Analysis of a Harmonically Morphing Airfoil Using Dynamic Meshing

This work explores the aerodynamic and aeroacoustic responses of an airfoil fitted with a harmonically morphing Trailing Edge Flap (TEF). An unsteady parametrization method adapted for harmonic is introduced, then coupled dynamic meshing to drive process. The turbulence characteristics are calculated using hybrid Stress Blended Eddy Simulation (SBES) RANS-LES model. far-field tonal noise predicted Ffowcs-Williams Hawkings (FW-H) acoustic analogy corrections account spanwise effects correlation length half chord. At various frequencies amplitudes, 2D spectra obtained NACA 0012 at low angle attack (AoA = 4°), Reynolds number 0.62 × 106, Mach 0.115, respectively, dominant correctly. coefficients un-morphed configuration show good agreement published experimental 3D LES data. For TEF case, results that it possible achieve up 3% increase in efficiency (L/D). Furthermore, slightly shifts predominant peak higher frequencies, possibly due causing breakup large-scale shed vortices into smaller, frequency turbulent eddies. It appears larger amplitudes induce sound pressure levels (SPLs), all cases shift main frequency, maximum 1.5 dB reduction SPL. proposed approach incorporating SBES model provides reasonable estimation affordable computational cost. Thus, can be used as efficient numerical tool predict emitted from wing design stage.