Name
Begins with
OR
contains
AND
Maximum Lift (CL)between and  (at Re=100,000)
Maximum Lift-to-drag (L/D)between and
Thicknessbetween and
Camberbetween and
Maximum number to show:

Number of items found : 1524 (showing the first 50)

Name Thickness (%) Camber (%) Lift Coeff. Lift-to-Drag (L/D) Stall Angle (deg) TE Angle (deg) LE Radius (%)
FX 77-W-270 27.0 4.3 0.283 2.1 -0.5 70.7 6.1
YS-900 9.0 0.0 0.311 11.6 5.5 19.8 1.5
NASA SC(2)-0402 AIRFOIL 2.0 0.2 0.328 20.2 3.5 5.1 1.3
NASA SC(2)-0403 AIRFOIL 3.0 0.4 0.408 19.4 5.0 6.3 1.3
NACA 2415 15.0 2.0 0.410 7.4 8.0 30.2 3.3
NASA SC(2)-0503 AIRFOIL 3.0 0.2 0.435 23.9 4.5 6.5 1.3
NACA 23021 21.0 2.4 0.443 6.6 7.5 44.5 4.9
NACA 2418 18.0 2.0 0.459 7.2 7.5 36.4 4.0
HQ 0/7 AIRFOIL 7.0 0.0 0.475 29.5 3.0 5.0 1.6
NASA SC(2)-0404 AIRFOIL 4.0 0.5 0.495 18.5 6.0 7.4 1.4
NACA 2421 21.0 2.0 0.501 7.3 7.5 42.4 4.7
GOE 443 AIRFOIL 5.0 0.0 0.512 30.1 3.0 7.4 1.5
GOE 444 AIRFOIL 5.6 0.0 0.515 31.6 3.5 10.3 1.5
NACA 16-006 6.0 0.0 0.524 23.3 2.5 17.4 1.5
NACA 16009 9.0 0.0 0.537 23.3 3.0 26.4 1.6
NACA 63-206 6.0 1.1 0.539 19.0 -0.5 3.2 1.5
BOEING-VERTOL VR-9 AIRFOIL 6.0 0.3 0.540 15.8 9.5 6.3 1.6
EPPLER 379 AIRFOIL 2.2 8.0 0.545 73.3 -0.5 2.8 1.7
EPPLER 874 HYDROFOIL AIRFOIL 7.9 1.0 0.547 33.1 3.0 15.1 1.7
GOE 445 AIRFOIL 6.4 0.0 0.552 40.2 4.0 10.3 1.6
HQ 0/9 AIRFOIL 8.1 0.0 0.552 34.0 4.0 5.8 1.8
Eh 1.0/7.0 7.0 1.0 0.567 41.2 3.5 5.7 1.6
EPPLER 340 AIRFOIL 13.7 2.6 0.571 10.1 3.0 15.0 2.5
FX 66-H-60 6.0 1.7 0.572 40.3 4.5 7.2 1.6
EPPLER 904 AIRFOIL 9.0 1.3 0.577 42.1 2.5 14.1 1.6
LWK 80-080 8.1 0.0 0.580 34.4 3.5 12.0 1.7
HT08 5.0 0.0 0.581 19.3 3.0 12.7 1.7
NACA 0008-34 8.0 0.0 0.586 26.2 3.0 17.4 1.7
HT12 5.0 0.0 0.588 23.8 3.5 8.9 1.7
HT05 4.8 0.0 0.590 18.0 2.5 16.8 1.7
NACA 64-008A AIRFOIL 8.0 0.0 0.599 13.7 1.5 10.4 1.7
R140 (original) 12.0 0.4 0.600 34.1 3.0 17.1 1.9
GOE 9K AIRFOIL 2.4 0.9 0.611 71.3 4.5 7.3 1.4
YS-915 9.1 1.8 0.612 34.0 -0.5 15.0 1.6
E184 (8.33%) 8.3 1.2 0.616 34.3 6.0 5.5 1.8
NACA 0006 6.0 0.0 0.616 21.4 2.5 10.6 1.8
NACA 66-206 6.0 1.1 0.620 26.8 8.0 6.0 1.5
EPPLER 297 AIRFOIL 11.3 0.0 0.625 50.8 4.5 7.2 2.0
NACA 65-206 6.0 1.1 0.627 26.3 1.0 4.5 1.5
EH 0.0/9.0 9.0 0.0 0.627 37.7 4.5 7.4 1.9
S1010 HPV airfoil 6.0 0.0 0.627 39.4 5.0 6.2 1.9
EH 2.0/7.0 7.0 2.0 0.635 54.8 4.5 5.7 1.6
MH 22 7.2% 7.2 1.8 0.635 64.1 4.5 6.6 1.7
E230 (9.96%) 10.0 0.0 0.636 33.9 6.0 8.6 2.2
NACA 64-206 6.0 1.1 0.639 26.8 0.5 3.6 1.5
NACA 0010-35 10.0 0.0 0.642 20.9 3.0 28.6 1.8
ONERA OA206 AIRFOIL 6.0 0.8 0.643 31.2 4.5 7.1 1.6
NACA-M1 AIRFOIL 6.2 0.0 0.644 12.4 1.5 17.4 1.9
GOE 780 AIRFOIL 11.9 1.0 0.649 31.4 0.5 22.6 1.8
NASA SC(2)-0406 AIRFOIL 6.0 0.3 0.664 21.6 2.0 10.4 1.6