Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(goe744-il) GOE 744 AIRFOIL | Gottingen 744 airfoil Max thickness 14.5% at 20% chord Max camber 7% at 30% chord | Remove Airfoil details Airfoil plotter |
(clarkys-il) CLARK YS AIRFOIL | CLARK YS airfoil Max thickness 11.7% at 30% chord Max camber 2.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(e555-il) EPPLER 555 AIRFOIL | Eppler E555 general aviation airfoil Max thickness 16% at 31.9% chord Max camber 2.6% at 67.4% chord | Remove Airfoil details Airfoil plotter |
(e169-il) E169 (14.4%) | Eppler E169 low Reynolds number airfoil Max thickness 14.4% at 26.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ah21-7-il) AH21 7% version (Andrew Hollom) | Andrew Hollom AH 21 airfoil (7% version) Max thickness 9% at 34.9% chord Max camber 2.3% at 54.8% chord | Remove Airfoil details Airfoil plotter |
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11 | HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord Max camber 2.7% at 52.1% chord | Remove Airfoil details Airfoil plotter |
(s5010-il) S5010 | Selig S5010 low Reynolds number airfoil Max thickness 9.8% at 27.6% chord Max camber 1.8% at 32% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe744-il,clarkys-il,e555-il,e169-il,ah21-7-il,cp-060-050-gn,s5010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe744-il | 50,000 | 9 | 3.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 50,000 | 5 | 7.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 100,000 | 9 | 5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 100,000 | 5 | 35.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 200,000 | 9 | 56.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 200,000 | 5 | 64.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 500,000 | 9 | 98.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 500,000 | 5 | 97.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe744-il | 1,000,000 | 9 | 128.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe744-il | 1,000,000 | 5 | 114.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 50,000 | 9 | 23.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 50,000 | 5 | 31.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 100,000 | 9 | 45.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 100,000 | 5 | 47 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 200,000 | 9 | 62.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 200,000 | 5 | 58.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 500,000 | 9 | 76.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 500,000 | 5 | 68.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkys-il | 1,000,000 | 9 | 85.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkys-il | 1,000,000 | 5 | 80.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 50,000 | 9 | 27.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 50,000 | 5 | 32.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 100,000 | 9 | 51.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 100,000 | 5 | 51.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 200,000 | 9 | 69.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 200,000 | 5 | 67.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 500,000 | 9 | 93.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 500,000 | 5 | 86.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e555-il | 1,000,000 | 9 | 110.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e555-il | 1,000,000 | 5 | 99.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 50,000 | 9 | 16.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 50,000 | 5 | 27 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 100,000 | 9 | 39.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 100,000 | 5 | 41.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 200,000 | 9 | 56.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 200,000 | 5 | 55.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 500,000 | 9 | 77.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 500,000 | 5 | 71.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e169-il | 1,000,000 | 9 | 92.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e169-il | 1,000,000 | 5 | 79.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 50,000 | 9 | 35.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 5 | 51.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 9 | 78.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 5 | 69.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 9 | 111.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 5 | 82.9 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 5 | 84.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 50,000 | 9 | 19.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 50,000 | 5 | 20.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 50,000 | 1 | 21.2 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 9 | 22.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 5 | 25 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 1 | 28 at α=10° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 9 | 26.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 5 | 31.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 1 | 35.7 at α=10.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 9 | 35.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 5 | 45.2 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 1 | 50 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 9 | 51.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 5 | 60.1 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 1 | 64.2 at α=11.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| s5010-il | 50,000 | 9 | 24.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 50,000 | 5 | 32.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 9 | 45 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 100,000 | 5 | 47.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 9 | 63.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 200,000 | 5 | 62.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 9 | 86.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 500,000 | 5 | 80.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 9 | 102.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5010-il | 1,000,000 | 5 | 94.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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