Discrete tonal noise of NACA0015 airfoil at low reynolds number
This paper is a pilot study of the effect of external forcing and passive control on the generation of airfoil whistle noise. Interaction between instability travelling inside laminar boundary layer with the airfoil trailing edge produces discrete tonal noise. This phenomenon commonly found at lo...
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Penerbit Akademia Baru
2019
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| Online Access: | http://irep.iium.edu.my/69941/ http://irep.iium.edu.my/69941/ http://irep.iium.edu.my/69941/1/69941_Discrete%20Tonal%20Noise%20of%20NACA0015.pdf http://irep.iium.edu.my/69941/7/69941_Discrete%20tonal%20noise_scopus.pdf |
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iium-699412019-07-09T08:35:32Z http://irep.iium.edu.my/69941/ Discrete tonal noise of NACA0015 airfoil at low reynolds number Andan, Amelda Dianne Lee, Duck-Joo TL500 Aeronautics This paper is a pilot study of the effect of external forcing and passive control on the generation of airfoil whistle noise. Interaction between instability travelling inside laminar boundary layer with the airfoil trailing edge produces discrete tonal noise. This phenomenon commonly found at low-to-moderate Reynolds numbers. The characteristics and behavior of tonal emissions at low Reynolds number differs from that at higher Reynolds number. Therefore, the purpose of this work is to study the discrete tonal noise generated by laminar boundary layer instability at low Reynolds number as well as at a variation of angle of attack. Experimental testing on NACA0015 was done in the anechoic wind tunnel to measure the sound spectrum at Reynolds number of Re~104 and angle of attack of 0°≤α≤5°. This work is intended to provide additional information to the tonal behavior of NACA series airfoil. Flow separation without reattachment occurs on the suction side within the selected Reynolds number and angle of attack. No tonal sound was found if fs falls below 40dB. At low Reynolds number, airfoil discrete tone consists of high intensity fs accompanied by more pronounced fn as freestream velocity increases. Airfoil tonal noise gradually decreases as angle of attack increases from α=0^° before disappearing beyond α=5°. Moreover, previously proposed empirical models to predict fs were found to have limitation in predicting tonal frequency at low Reynolds number at a variation of angle of attack. In addition, general observation shows fn has a velocity dependency of ~U0.8 while f_s is prone to exhibit ladder structure behavior with velocity dependency of ~U1.3. Penerbit Akademia Baru 2019 Article PeerReviewed application/pdf en http://irep.iium.edu.my/69941/1/69941_Discrete%20Tonal%20Noise%20of%20NACA0015.pdf application/pdf en http://irep.iium.edu.my/69941/7/69941_Discrete%20tonal%20noise_scopus.pdf Andan, Amelda Dianne and Lee, Duck-Joo (2019) Discrete tonal noise of NACA0015 airfoil at low reynolds number. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 53 (1). pp. 129-145. ISSN 2289-7879 http://www.akademiabaru.com/doc/ARFMTSV53_N1_P129_145.pdf |
| repository_type |
Digital Repository |
| institution_category |
Local University |
| institution |
International Islamic University Malaysia |
| building |
IIUM Repository |
| collection |
Online Access |
| language |
English English |
| topic |
TL500 Aeronautics |
| spellingShingle |
TL500 Aeronautics Andan, Amelda Dianne Lee, Duck-Joo Discrete tonal noise of NACA0015 airfoil at low reynolds number |
| description |
This paper is a pilot study of the effect of external forcing and passive control on the
generation of airfoil whistle noise. Interaction between instability travelling inside
laminar boundary layer with the airfoil trailing edge produces discrete tonal noise. This
phenomenon commonly found at low-to-moderate Reynolds numbers. The
characteristics and behavior of tonal emissions at low Reynolds number differs from
that at higher Reynolds number. Therefore, the purpose of this work is to study the
discrete tonal noise generated by laminar boundary layer instability at low Reynolds
number as well as at a variation of angle of attack. Experimental testing on NACA0015
was done in the anechoic wind tunnel to measure the sound spectrum at Reynolds
number of Re~104 and angle of attack of 0°≤α≤5°. This work is intended to provide
additional information to the tonal behavior of NACA series airfoil. Flow separation
without reattachment occurs on the suction side within the selected Reynolds number
and angle of attack. No tonal sound was found if fs falls below 40dB. At low Reynolds
number, airfoil discrete tone consists of high intensity fs accompanied by more
pronounced fn as freestream velocity increases. Airfoil tonal noise gradually decreases
as angle of attack increases from α=0^° before disappearing beyond α=5°. Moreover,
previously proposed empirical models to predict fs were found to have limitation in
predicting tonal frequency at low Reynolds number at a variation of angle of attack. In
addition, general observation shows fn has a velocity dependency of ~U0.8 while f_s is
prone to exhibit ladder structure behavior with velocity dependency of ~U1.3. |
| format |
Article |
| author |
Andan, Amelda Dianne Lee, Duck-Joo |
| author_facet |
Andan, Amelda Dianne Lee, Duck-Joo |
| author_sort |
Andan, Amelda Dianne |
| title |
Discrete tonal noise of NACA0015 airfoil at low reynolds
number |
| title_short |
Discrete tonal noise of NACA0015 airfoil at low reynolds
number |
| title_full |
Discrete tonal noise of NACA0015 airfoil at low reynolds
number |
| title_fullStr |
Discrete tonal noise of NACA0015 airfoil at low reynolds
number |
| title_full_unstemmed |
Discrete tonal noise of NACA0015 airfoil at low reynolds
number |
| title_sort |
discrete tonal noise of naca0015 airfoil at low reynolds
number |
| publisher |
Penerbit Akademia Baru |
| publishDate |
2019 |
| url |
http://irep.iium.edu.my/69941/ http://irep.iium.edu.my/69941/ http://irep.iium.edu.my/69941/1/69941_Discrete%20Tonal%20Noise%20of%20NACA0015.pdf http://irep.iium.edu.my/69941/7/69941_Discrete%20tonal%20noise_scopus.pdf |
| first_indexed |
2023-09-18T21:39:16Z |
| last_indexed |
2023-09-18T21:39:16Z |
| _version_ |
1777413030143852544 |