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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(goe436-il) GOE 436 AIRFOIL | Gottingen 436 airfoil Max thickness 11% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(s808-nr) NREL's S808 Airfoil | NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord | Remove Airfoil details Airfoil plotter |
(mh45-il) MH 45 9.85% | Martin Hepperle MH 45 for flying wings Max thickness 9.8% at 26.9% chord Max camber 1.7% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(raf15-il) RAF 15 AIRFOIL | RAF-15 airfoil Max thickness 6.5% at 15% chord Max camber 2.6% at 30% chord | Remove Airfoil details Airfoil plotter |
(mh43-il) MH 43 8.5% | Martin Hepperle MH 43 for F3B and F3E Max thickness 8.5% at 31.4% chord Max camber 1.7% at 36.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe436-il,s808-nr,mh45-il,raf15-il,mh43-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe436-il | 50,000 | 9 | 23.5 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 50,000 | 5 | 34.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 100,000 | 9 | 47.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 100,000 | 5 | 51.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 200,000 | 9 | 68.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 200,000 | 5 | 69.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 500,000 | 9 | 96.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 500,000 | 5 | 92.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe436-il | 1,000,000 | 9 | 118.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe436-il | 1,000,000 | 5 | 108.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 50,000 | 9 | 8.2 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 50,000 | 5 | 24.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 100,000 | 9 | 36.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 100,000 | 5 | 41.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 200,000 | 9 | 55.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 200,000 | 5 | 56 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 500,000 | 9 | 78.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 500,000 | 5 | 76.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 1,000,000 | 9 | 98.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 1,000,000 | 5 | 92.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 50,000 | 9 | 27.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 50,000 | 5 | 32.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 9 | 44.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 5 | 45.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 9 | 60.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 5 | 58.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 9 | 81.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 5 | 75.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 9 | 95.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 5 | 88.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 50,000 | 9 | 32.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 50,000 | 5 | 33.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 100,000 | 9 | 43.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 100,000 | 5 | 47.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 200,000 | 9 | 59.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 200,000 | 5 | 59.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 500,000 | 9 | 78.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 500,000 | 5 | 76.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf15-il | 1,000,000 | 9 | 92.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf15-il | 1,000,000 | 5 | 89.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh43-il | 50,000 | 9 | 33.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh43-il | 50,000 | 5 | 35.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh43-il | 100,000 | 9 | 50.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh43-il | 100,000 | 5 | 49.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh43-il | 200,000 | 9 | 66.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh43-il | 200,000 | 5 | 61.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh43-il | 500,000 | 9 | 86.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh43-il | 500,000 | 5 | 76.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh43-il | 1,000,000 | 9 | 100 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh43-il | 1,000,000 | 5 | 85.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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