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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(nacam18-il) NACA M18 | NACA M18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(nlf1015-il) NASA NLF1015 | NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil Max thickness 15% at 39.8% chord Max camber 4.3% at 62.8% chord | Remove Airfoil details Airfoil plotter |
(mh120-il) MH 120 11.57% | Martin Hepperle MH 120 for tip section of a propeller Max thickness 11.6% at 34.7% chord Max camber 2.2% at 44.2% chord | Remove Airfoil details Airfoil plotter |
(ah94145-il) AH 94-145 | Althaus AH 94-145 airfoil Max thickness 14.6% at 38.9% chord Max camber 5.6% at 44.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nacam18-il,nlf1015-il,mh120-il,ah94145-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacam18-il | 50,000 | 9 | 10.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 50,000 | 5 | 26.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 100,000 | 9 | 47.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 100,000 | 5 | 50.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 200,000 | 9 | 71.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 200,000 | 5 | 72.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 500,000 | 9 | 102.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 500,000 | 5 | 99.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 1,000,000 | 9 | 125.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 1,000,000 | 5 | 114 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 50,000 | 9 | 25.8 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 50,000 | 5 | 21.9 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 100,000 | 9 | 40.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 100,000 | 5 | 38.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 200,000 | 9 | 75.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 200,000 | 5 | 77.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 500,000 | 9 | 130.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 500,000 | 5 | 125.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 1,000,000 | 9 | 167.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 1,000,000 | 5 | 154.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 50,000 | 9 | 32.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 50,000 | 5 | 34.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 100,000 | 9 | 54.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 100,000 | 5 | 54.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 200,000 | 9 | 76.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 200,000 | 5 | 73.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 500,000 | 9 | 104.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 500,000 | 5 | 95.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 1,000,000 | 9 | 124.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 1,000,000 | 5 | 105.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 50,000 | 9 | 6.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 50,000 | 5 | 14.8 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 9 | 28 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 5 | 30.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 9 | 75.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 5 | 81.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 9 | 135.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 5 | 132.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 9 | 177.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 5 | 164.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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