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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(usa31-il) USA 31 AIRFOIL | USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(n64212mb-il) NACA 64(1)-212 MOD B | NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord | Remove Airfoil details Airfoil plotter |
(hq158-il) HQ 1.5/8 AIRFOIL | Quabeck HQ 1.5/8 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca633018-il) NACA 63(3)-018 | NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa31-il,n64212mb-il,hq158-il,naca633018-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa31-il | 50,000 | 9 | 4.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 50,000 | 5 | 14.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 9 | 34.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 100,000 | 5 | 40.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 9 | 62.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 200,000 | 5 | 54.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 9 | 76.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 500,000 | 5 | 69.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 9 | 88.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa31-il | 1,000,000 | 5 | 79.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212mb-il | 50,000 | 9 | 24.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212mb-il | 50,000 | 5 | 25.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212mb-il | 100,000 | 9 | 30.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212mb-il | 100,000 | 5 | 35.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212mb-il | 200,000 | 9 | 45.8 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212mb-il | 200,000 | 5 | 51.3 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212mb-il | 500,000 | 9 | 74.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212mb-il | 500,000 | 5 | 76.5 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64212mb-il | 1,000,000 | 9 | 96.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64212mb-il | 1,000,000 | 5 | 95 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 50,000 | 9 | 35.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 50,000 | 5 | 35.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 100,000 | 9 | 51.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 100,000 | 5 | 49 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 200,000 | 9 | 68.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 200,000 | 5 | 60.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 500,000 | 9 | 86.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 500,000 | 5 | 70 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq158-il | 1,000,000 | 9 | 92 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq158-il | 1,000,000 | 5 | 77.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 9 | 23.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 50,000 | 5 | 20.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 9 | 40.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 100,000 | 5 | 36.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 9 | 53.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 200,000 | 5 | 50.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 500,000 | 5 | 61.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 9 | 83 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca633018-il | 1,000,000 | 5 | 65.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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