Abstract

This paper further analyzes results of airfoil self-noise prediction obtained with large eddy simulations in previous work. The primary interest consists of evaluating the eects of mean ow and quadrupole sources for the noise prediction of a NACA0012 airfoil at low and moderate freestream Mach numbers using the Ffowcs Williams & Hawkings (FWH) equation. The Reynolds number based on the airfoil chord is xed at Rec = 408;000. A combination of laminar and turbulent boundary layers on suction and pressure side, as well as trailing edge bluntness, are the physical mechanisms responsible for noise generation in the aerodynamic ows analyzed. From the present results, it is observed that vortex shedding occurs due to either laminar boundary layer separation or trailing edge bluntness. Visualization of this physical mechanism for blunt trailing edges requires a careful analysis. The FWH analogy is used for the acoustic predictions and it is found that, for low Mach number ows, quadrupole sources can be neglected in the FWH equation. However, for

Talk to us

Join us for a 30 min session where you can share your feedback and ask us any queries you have

Schedule a call

Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.