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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(supermarine371ii-il) Supermarine 371-II (tip) | Supermarine 371-II tip airfoil Max thickness 8.4% at 50% chord Max camber 0.9% at 45% chord | Remove Airfoil details Airfoil plotter |
(naca23012-il) NACA 23012 12% | NACA 23012 airfoil Max thickness 12% at 29.8% chord Max camber 1.8% at 12.7% chord | Remove Airfoil details Airfoil plotter |
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL | NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% chord | Remove Airfoil details Airfoil plotter |
(lwk79100-il) LWK 79-100 | LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca2410-il) NACA 2410 | NACA 2410 airfoil Max thickness 10% at 29.9% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
(mh25-il) MH 25 9.98% | Martin Hepperle MH 25 for F3D Pylon Racing (extended laminar flow) Max thickness 10% at 42.2% chord Max camber 1.4% at 42.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (supermarine371ii-il,naca23012-il,nlf416-il,lwk79100-il,naca2410-il,mh25-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| supermarine371ii-il | 50,000 | 9 | 19.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 50,000 | 5 | 23.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 100,000 | 9 | 29.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 100,000 | 5 | 37.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 200,000 | 9 | 51.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 200,000 | 5 | 45.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 500,000 | 9 | 63.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 500,000 | 5 | 54.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| supermarine371ii-il | 1,000,000 | 9 | 73.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| supermarine371ii-il | 1,000,000 | 5 | 58.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 50,000 | 9 | 24.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 50,000 | 5 | 28.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 100,000 | 9 | 36.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 100,000 | 5 | 40.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 200,000 | 9 | 51 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 200,000 | 5 | 55.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 500,000 | 9 | 77.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 500,000 | 5 | 77.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23012-il | 1,000,000 | 9 | 96.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23012-il | 1,000,000 | 5 | 93.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 50,000 | 9 | 14.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 50,000 | 5 | 25.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 100,000 | 9 | 45.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 100,000 | 5 | 48.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 200,000 | 9 | 65.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 200,000 | 5 | 67.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 500,000 | 9 | 93.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 500,000 | 5 | 91.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf416-il | 1,000,000 | 9 | 115.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf416-il | 1,000,000 | 5 | 108.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 50,000 | 9 | 25.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 9 | 37.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 5 | 35.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 9 | 47.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 5 | 44.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 9 | 59.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 5 | 60.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 9 | 72.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 5 | 74.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 50,000 | 9 | 35.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 50,000 | 5 | 36.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 9 | 51.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 100,000 | 5 | 49.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 9 | 67.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 200,000 | 5 | 62 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 9 | 86.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 500,000 | 5 | 75.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 9 | 98.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2410-il | 1,000,000 | 5 | 83.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 50,000 | 9 | 34.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 50,000 | 5 | 32.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 100,000 | 9 | 51.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 100,000 | 5 | 48 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 200,000 | 9 | 70.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 200,000 | 5 | 58.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 500,000 | 9 | 78.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 500,000 | 5 | 60.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh25-il | 1,000,000 | 9 | 75 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh25-il | 1,000,000 | 5 | 69.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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