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 79-W-660A 66.4 2.3 2.013 11.2 2.0 158.2 20.1
FX 79-W-470A 46.3 3.8 1.727 11.0 1.0 148.6 12.2
EPPLER 864 STRUT AIRFOIL 38.8 0.0 1.384 13.8 3.0 61.4 10.9
EPPLER 863 STRUT AIRFOIL 35.7 0.0 1.326 14.2 2.5 55.0 9.8
WORTMANN FX 77-W-343 AIRFOIL 34.2 4.7 1.374 9.4 -0.5 73.1 9.3
GOE 570 AIRFOIL 33.6 9.6 2.416 42.5 -0.5 49.2 10.7
EPPLER 862 STRUT AIRFOIL 32.3 0.0 1.318 14.8 2.0 48.0 8.7
Griffith 30% Suction Airfoil 30.5 0.0 1.588 29.1 1.5 13.0 4.7
AH 94-W-301 30.1 1.1 1.442 17.1 -0.5 53.4 7.3
AH 93-W-300 30.0 1.1 1.516 17.8 -0.5 48.4 10.8
FX 69-PR-281 28.1 5.6 2.154 39.2 -0.5 16.1 12.3
KENNEDY AND MARSDEN AIRFOIL 27.9 7.7 2.646 55.4 -0.5 8.6 9.1
Marsden 27.8 9.6 2.809 59.3 -5.5 8.6 8.8
FX 69-274 27.4 3.2 1.342 21.9 1.5 47.3 5.9
FX 77-W-270S 27.0 4.3 1.265 13.1 0.0 54.7 6.1
FX 77-W-270 27.0 4.3 0.283 2.1 -0.5 70.7 6.1
WORTMANN FX 77-W-258 AIRFOIL 26.1 4.3 1.652 15.8 -0.5 37.9 6.0
GOE 435 AIRFOIL 26.0 4.7 2.037 33.4 -0.5 21.4 9.1
SIKORSKY DBLN-526 AIRFOIL 25.9 4.0 2.240 57.9 -0.5 113.0 5.1
TH 25816 HALE AIRFOIL 25.7 4.0 2.175 45.4 -0.5 22.8 4.0
AH 93-W-257 25.6 1.8 1.641 23.4 -0.5 27.7 5.3
GOE 776 AIRFOIL 24.9 0.3 1.297 24.3 2.5 42.0 7.5
GOE 561 AIRFOIL 24.9 10.2 2.234 40.5 -0.5 42.7 7.9
RAF 89 AIRFOIL 24.8 1.6 1.582 30.7 -0.5 26.8 7.9
GOE 571 AIRFOIL 24.8 9.8 2.248 40.0 -0.5 38.6 7.6
NACA 0024 23.9 0.0 1.284 25.3 3.0 40.6 7.1
NACA 2424 23.9 2.0 1.580 37.0 0.5 35.7 7.5
NACA 23024 23.9 1.9 1.360 29.9 1.5 35.8 7.8
MH 150 23.89% 23.9 5.4 2.056 41.4 -0.5 0.7 5.2
GOE 434 AIRFOIL 22.7 5.1 2.042 38.8 -0.5 18.7 8.2
EPPLER 858 AIRFOIL 22.6 4.8 1.945 48.0 2.5 23.6 4.7
FX 83-W-227 22.6 3.4 1.799 38.3 -0.5 26.2 4.6
B-29 ROOT AIRFOIL 22.0 1.7 1.399 25.4 0.5 25.0 5.1
FX 84-W-218 21.9 3.2 1.719 35.0 -0.5 9.9 5.0
GOE 777 AIRFOIL 21.9 5.9 1.789 29.4 -0.5 27.4 6.0
AH 81-K-144 W-F KLAPPE 21.7 1.1 1.064 11.4 2.0 24.9 6.8
GOE 522 AIRFOIL 21.7 5.2 2.060 47.1 -0.5 21.0 6.7
AH 93-W-215 21.2 3.1 1.761 32.8 -0.5 26.5 4.5
NACA 4421 21.0 4.0 1.285 86.3 -0.5 31.3 4.8
NACA 23021 21.0 2.4 0.443 6.6 7.5 44.5 4.9
NACA 2421 21.0 2.0 0.501 7.3 7.5 42.4 4.7
NACA 66-021 AIRFOIL 21.0 0.0 1.088 27.1 1.5 16.3 3.3
NACA 66(4)-221 21.0 1.1 1.251 31.4 -0.5 16.3 3.4
NACA 65(4)-221 21.0 1.1 1.273 30.9 -0.5 12.4 3.6
NACA 65(4)-421 21.0 2.2 1.438 34.2 -0.5 12.4 3.7
NACA 65(4)-421 a=0.5 21.0 3.0 1.400 30.4 -0.5 12.4 3.7
NACA 64(4)-421 20.9 2.2 1.545 32.9 -0.5 10.2 4.1
NACA 64(4)-221 20.9 1.1 1.369 29.5 -0.5 10.3 4.0
NACA 63(4)-221 20.9 1.1 1.438 32.5 -0.5 9.0 4.2
NACA 63(4)-421 20.9 2.2 1.634 34.1 -0.5 8.9 4.3