Please use this identifier to cite or link to this item:
|Scopus||Web of Science®||Altmetric|
|Title:||A comparison of NACA 0012 and NACA 0021 self-noise at low Reynolds number|
|Citation:||Fluid-Structure-Sound Interactions and Control. Proceedings of the 3rd Symposium on Fluid-Structure-Sound Interactions and Control (FSSIC), as published in Lecture Notes in Mechanical Engineering, 2016 / Zhou, Y., Lucey, A.D., Liu, Y., Huang, L. (ed./s), pp.21-25|
|Series/Report no.:||Lecture Notes in Mechanical Engineering|
|Conference Name:||3rd Symposium on Fluid-Structure-Sound Interactions and Control (05 Jul 2015 - 09 Jul 2015 : Perth, Australia)|
|A. Laratro, M. Arjomandi, B. Cazzolato and R. Kelso|
|Abstract:||The self-noise of NACA 0012 and NACA 0021 airfoils are recorded at a Reynolds numbers of 96,000 in an anechoic wind tunnel at an angle-of-attack range of −5∘–40∘. Results suggest that the low angle-of-attack tonal noise of the airfoils behaves differently, with the NACA 0021 producing tones at much higher angles-of-attack but not near 0∘. Noise generated at the onset of stall is subtlely different, with signature of the NACA 0012 forming over a larger angular range compared to the NACA 0021 where the stall signature forms suddenly.|
|Keywords:||Aeroacoustics; Stall noise; Airfoil noise|
|Rights:||© Springer-Verlag Berlin Heidelberg 2016|
|Appears in Collections:||Mechanical Engineering publications|
Files in This Item:
There are no files associated with this item.
Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.