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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(raf89-il) RAF 89 AIRFOIL | RAF-89 airfoil Max thickness 25% at 30% chord Max camber 1.6% at 50% chord | Remove Airfoil details Airfoil plotter |
(raf26-il) RAF 26 AIRFOIL | RAF-26 airfoil Max thickness 6.6% at 29.9% chord Max camber 2.1% at 49.9% chord | Remove Airfoil details Airfoil plotter |
(usa98-il) USA 98 AIRFOIL | USA-98 airfoil Max thickness 14.3% at 30% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(rc510-il) NASA RC(5)-10 AIRFOIL | NASA/Langley RC(5)-10 rotorcraft airfoil Max thickness 10% at 40.1% chord Max camber 2.2% at 25.3% chord | Remove Airfoil details Airfoil plotter |
(mh112-il) MH 112 Airfoil | Martin Hepperle MH 112 for a propeller for ultralight (root) Max thickness 16.2% at 31.8% chord Max camber 6.7% at 48.5% chord | Remove Airfoil details Airfoil plotter |
(raf38-il) RAF 38 AIRFOIL | RAF-38 airfoil Max thickness 12.7% at 30% chord Max camber 2.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf89-il,raf26-il,usa98-il,rc510-il,mh112-il,raf38-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf89-il | 50,000 | 9 | 1.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 50,000 | 5 | 7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 9 | 18.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 5 | 27.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 9 | 45.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 5 | 36 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 9 | 50.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 5 | 39.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 9 | 56.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 5 | 45.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 50,000 | 9 | 34 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 50,000 | 5 | 37.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 100,000 | 9 | 53.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 100,000 | 5 | 51.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 200,000 | 9 | 71.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 200,000 | 5 | 62.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 500,000 | 9 | 88.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 500,000 | 5 | 69.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 1,000,000 | 9 | 94.1 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 1,000,000 | 5 | 76.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 9 | 8.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 5 | 26.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 9 | 54.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 5 | 59.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 9 | 84.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 5 | 84.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 9 | 120.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 5 | 112.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 9 | 147.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 5 | 124.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 9 | 31.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 5 | 32.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 9 | 46.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 5 | 43.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 9 | 60.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 5 | 54.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 9 | 76.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 5 | 75.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 9 | 94.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 5 | 92.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 50,000 | 9 | 5.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 50,000 | 5 | 14.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 100,000 | 9 | 37.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 100,000 | 5 | 48.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 200,000 | 9 | 80 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 200,000 | 5 | 79.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 500,000 | 9 | 120 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 500,000 | 5 | 109.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh112-il | 1,000,000 | 9 | 147.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh112-il | 1,000,000 | 5 | 126.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 50,000 | 9 | 31.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 50,000 | 5 | 32.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 100,000 | 9 | 51.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 100,000 | 5 | 51.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 200,000 | 9 | 71.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 200,000 | 5 | 69 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 500,000 | 9 | 96.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 500,000 | 5 | 90.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 1,000,000 | 9 | 114.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 1,000,000 | 5 | 98.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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