Effects of internal Acoustic Excitation on the Improvement of 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 co...
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| Formato: | article |
| Lenguaje: | EN |
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Al-Khwarizmi College of Engineering – University of Baghdad
2007
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| Acceso en línea: | https://doaj.org/article/8ea9d0231a7749d9b62ba1d04aac19ab |
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