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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(lrn1007-il) lrn1007 | LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord Max camber 5.9% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(apex16-il) Apex 16 (normalized using XFOIL date021206) | Drela Apex 16 low Reynolds number transonic research airfoil Max thickness 12.9% at 38.6% chord Max camber 2.4% at 59.6% 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 |
(oaf102-il) OAF102 AIRFOIL | ONERA/Aerospatiale OAF102 Fenestron airfoil Max thickness 10.2% at 28.7% chord Max camber 3.6% at 53.1% chord | Remove Airfoil details Airfoil plotter |
(sa7025-il) SA7025 | Selig / Ashok Gopalarathnam SA7025 low Reynolds number airfoil Max thickness 8% at 29.2% chord Max camber 3.6% at 43.2% chord | Remove Airfoil details Airfoil plotter |
(sg6042-il) SG6042 | Selig / Giguere SG6042 wind turbine airfoil (high L/D) Max thickness 10% at 33.5% chord Max camber 3.3% at 51.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (lrn1007-il,apex16-il,ah94145-il,oaf102-il,sa7025-il,sg6042-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lrn1007-il | 50,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 50,000 | 5 | 35.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 9 | 51.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 5 | 55.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 9 | 81.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 5 | 98.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 9 | 125.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 5 | 150.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 1,000,000 | 9 | 127.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| apex16-il | 50,000 | 9 | 34 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| apex16-il | 50,000 | 5 | 32.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| apex16-il | 100,000 | 9 | 56.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| apex16-il | 100,000 | 5 | 54.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| apex16-il | 200,000 | 9 | 81.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| apex16-il | 200,000 | 5 | 76.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| apex16-il | 500,000 | 9 | 112.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| apex16-il | 500,000 | 5 | 92.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| apex16-il | 1,000,000 | 9 | 123.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| apex16-il | 1,000,000 | 5 | 99.4 at α=3.25° | 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 | |
| oaf102-il | 50,000 | 9 | 40.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 50,000 | 5 | 41.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 9 | 61.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 5 | 60.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 9 | 82.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 5 | 77.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 9 | 107.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 5 | 86.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 9 | 114 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 5 | 92 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 50,000 | 9 | 38.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 50,000 | 5 | 41.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 100,000 | 9 | 60.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 100,000 | 5 | 60.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 200,000 | 9 | 83.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 200,000 | 5 | 77.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 500,000 | 9 | 111.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 500,000 | 5 | 98.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7025-il | 1,000,000 | 9 | 129.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7025-il | 1,000,000 | 5 | 112.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 50,000 | 9 | 40 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 50,000 | 5 | 39.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 100,000 | 9 | 62.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 100,000 | 5 | 60.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 200,000 | 9 | 89 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 200,000 | 5 | 82.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 500,000 | 9 | 123.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 500,000 | 5 | 106.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sg6042-il | 1,000,000 | 9 | 145.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sg6042-il | 1,000,000 | 5 | 110.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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