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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(cp-180-050-gn) Cambered plate C=18% T=5% R=0.78 | HAWT pipe blade with coordinates based on top surface. Camber=18% Wall thickness=5% Radius=0.784 Max thickness 5% at 3.2% chord Max camber 16.4% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(goe184-il) GOE 184 (MVA H.29) AIRFOIL | Gottingen 184 (MVA H.29) airfoil Max thickness 8.3% at 19.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(sc1012r8-il) SIKORSKY SC1012R8 AIRFOIL | Sikorsky SC1012 R8 rotorcraft airfoil Max thickness 12% at 27.8% chord Max camber 2.7% at 21.8% chord | Remove Airfoil details Airfoil plotter |
(cp-140-050-gn) Cambered plate C=14% T=5% R=0.96 | HAWT pipe blade with coordinates based on top surface. Camber=14% Wall thickness=5% Radius=0.963 Max thickness 5.5% at 3.6% chord Max camber 12.2% at 47.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cp-180-050-gn,goe184-il,sc1012r8-il,cp-140-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-180-050-gn | 50,000 | 9 | 16.1 at α=17° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 50,000 | 5 | 13.5 at α=18.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 50,000 | 1 | 10.9 at α=10° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 100,000 | 9 | 15 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 100,000 | 5 | 15 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 100,000 | 1 | 16.7 at α=8.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 200,000 | 9 | 29.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 200,000 | 5 | 29.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 200,000 | 1 | 28.9 at α=5.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 500,000 | 9 | 55.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 500,000 | 5 | 46.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 500,000 | 1 | 33.5 at α=3° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-180-050-gn | 1,000,000 | 9 | 52.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-180-050-gn | 1,000,000 | 5 | 47.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-180-050-gn | 1,000,000 | 1 | 29.8 at α=2° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| goe184-il | 50,000 | 9 | 34 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 50,000 | 5 | 39.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 100,000 | 9 | 57.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 100,000 | 5 | 60.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 200,000 | 9 | 79.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 200,000 | 5 | 79.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 500,000 | 9 | 107.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 500,000 | 5 | 102.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 1,000,000 | 9 | 127.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 1,000,000 | 5 | 111.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 50,000 | 9 | 23.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 9 | 34 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 100,000 | 5 | 37.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 9 | 46.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 200,000 | 5 | 50.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 9 | 68.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 500,000 | 5 | 72.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 9 | 88.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc1012r8-il | 1,000,000 | 5 | 90.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-140-050-gn | 50,000 | 9 | 21.8 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-140-050-gn | 50,000 | 5 | 17 at α=14.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-140-050-gn | 50,000 | 1 | 15.6 at α=7.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-140-050-gn | 100,000 | 9 | 24.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-140-050-gn | 100,000 | 5 | 28 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-140-050-gn | 100,000 | 1 | 25.2 at α=5.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-140-050-gn | 200,000 | 9 | 52.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-140-050-gn | 200,000 | 5 | 42.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-140-050-gn | 200,000 | 1 | 34.6 at α=3° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-140-050-gn | 500,000 | 9 | 53.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-140-050-gn | 500,000 | 5 | 47.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-140-050-gn | 500,000 | 1 | 37.1 at α=6.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-140-050-gn | 1,000,000 | 9 | 47.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-140-050-gn | 1,000,000 | 5 | 45 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-140-050-gn | 1,000,000 | 1 | 46.3 at α=5.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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