Effects of internal Acoustic Excitation on the Improvementof Airfoil Performance
The effect of internal acoustic excitation on the leading-edge, separated boundary layers and the aerodynamic performance of NACA23015 cross section airfoil are examined as a function of excitation location with ranging frequency range (50-400) Hz of the introduced acoustic. Tests are separately con...
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| Format: | article |
| Langue: | EN |
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Al-Khwarizmi College of Engineering – University of Baghdad
2007
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| Accès en ligne: | https://doaj.org/article/d8b0587a497d427f9b3a7b7c8f5dae66 |
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