Abstract
This paper concerns the experimental verification of a new airfoil family for wind turbines. The family consist of airfoils in the relative thickness range from 15% to 30%. Three airfoils, Risoe-A1-18, Risoe-A1-21, and Risoe-A1-24 were tested in a wind tunnel. The verification consisted of both static and dynamic measurements. Here, the static results are presented for a Reynolds number of 1.6x10{sup 6} for the following airfoil configurations: smooth surface (all three airfoils) and Risoe-A1-24 mounted with leading edge roughness, vortex generators, and Gurney-flaps, respectively. All three airfoils have constant lift curve slope and almost constant drag coefficient until the maximum lift coefficient of about 1.4 is reached. The experimental results are compared with corresponding computational from the general purpose flow solver, EllipSys2D, showing good agreement. (au)
Citation Formats
Dahl, K S, Fuglsang, P, and Antoniou, I.
Experimental verification of the new RISOe-A1 airfoil family for wind turbines.
Denmark: N. p.,
1999.
Web.
Dahl, K S, Fuglsang, P, & Antoniou, I.
Experimental verification of the new RISOe-A1 airfoil family for wind turbines.
Denmark.
Dahl, K S, Fuglsang, P, and Antoniou, I.
1999.
"Experimental verification of the new RISOe-A1 airfoil family for wind turbines."
Denmark.
@misc{etde_679609,
title = {Experimental verification of the new RISOe-A1 airfoil family for wind turbines}
author = {Dahl, K S, Fuglsang, P, and Antoniou, I}
abstractNote = {This paper concerns the experimental verification of a new airfoil family for wind turbines. The family consist of airfoils in the relative thickness range from 15% to 30%. Three airfoils, Risoe-A1-18, Risoe-A1-21, and Risoe-A1-24 were tested in a wind tunnel. The verification consisted of both static and dynamic measurements. Here, the static results are presented for a Reynolds number of 1.6x10{sup 6} for the following airfoil configurations: smooth surface (all three airfoils) and Risoe-A1-24 mounted with leading edge roughness, vortex generators, and Gurney-flaps, respectively. All three airfoils have constant lift curve slope and almost constant drag coefficient until the maximum lift coefficient of about 1.4 is reached. The experimental results are compared with corresponding computational from the general purpose flow solver, EllipSys2D, showing good agreement. (au)}
place = {Denmark}
year = {1999}
month = {Mar}
}
title = {Experimental verification of the new RISOe-A1 airfoil family for wind turbines}
author = {Dahl, K S, Fuglsang, P, and Antoniou, I}
abstractNote = {This paper concerns the experimental verification of a new airfoil family for wind turbines. The family consist of airfoils in the relative thickness range from 15% to 30%. Three airfoils, Risoe-A1-18, Risoe-A1-21, and Risoe-A1-24 were tested in a wind tunnel. The verification consisted of both static and dynamic measurements. Here, the static results are presented for a Reynolds number of 1.6x10{sup 6} for the following airfoil configurations: smooth surface (all three airfoils) and Risoe-A1-24 mounted with leading edge roughness, vortex generators, and Gurney-flaps, respectively. All three airfoils have constant lift curve slope and almost constant drag coefficient until the maximum lift coefficient of about 1.4 is reached. The experimental results are compared with corresponding computational from the general purpose flow solver, EllipSys2D, showing good agreement. (au)}
place = {Denmark}
year = {1999}
month = {Mar}
}