This chapter summarises the results of 2D CFD simulations of a 30P30N aerofoil section (without a leading edge slat) equipped with a morphing trailing edge flap (TEF). Numerical simulations are carried out at a fixed angle of attack of 8°, with f lap deflections of 5° and 15°. Results demonstrate that at the lower angle of attack case, the morphing TEF is able to reduce noise without reducing aerodynamic efficiency. However, at the higher angle of attack case, the overall performance is similar to that of a flapped conventional configuration, except at the highest frequencies where the conventional configuration is slightly quieter.
Evaluating the Effects of a Morphed Trailing Edge Flap for Aeroacoustics Applications
Sustainable aviat.
International Symposium on Aviation Technology, MRO, and Operations ; 2021 ; Budapest, Hungary June 28, 2021 - June 30, 2021
2023-11-09
9 pages
Aufsatz/Kapitel (Buch)
Elektronische Ressource
Englisch