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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(clarym15-il) CLARK YM-15 AIRFOIL | CLARK YM15 airfoil Max thickness 15% at 29.6% chord Max camber 3.6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(as5046-il) AS5046 (16%) | AS5046 airfoil Ashok Gopalarathnam/Selig 16% airfoil Max thickness 16% at 37.6% chord Max camber 0.7% at 77.4% chord | Remove Airfoil details Airfoil plotter |
(as5045-il) AS5045 (15%) | AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil Max thickness 15% at 37.5% chord Max camber 1% at 27.2% chord | Remove Airfoil details Airfoil plotter |
(as5048-il) AS5048 (18%) | AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil Max thickness 18% at 38.3% chord Max camber 0.8% at 77.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (clarym15-il,as5046-il,as5045-il,as5048-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarym15-il | 50,000 | 9 | 12.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 50,000 | 5 | 31 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 9 | 47.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 5 | 48.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 9 | 66.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 5 | 62.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 9 | 88.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 5 | 84.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 9 | 109.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 5 | 105.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 50,000 | 9 | 28.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 50,000 | 5 | 28.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 100,000 | 9 | 42.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 100,000 | 5 | 42.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 200,000 | 9 | 58.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 200,000 | 5 | 55.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 500,000 | 9 | 77.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 500,000 | 5 | 69.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5046-il | 1,000,000 | 9 | 90.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5046-il | 1,000,000 | 5 | 83.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 50,000 | 9 | 30 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 50,000 | 5 | 29.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 100,000 | 9 | 44 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 100,000 | 5 | 43.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 200,000 | 9 | 59.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 200,000 | 5 | 56.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 500,000 | 9 | 79.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 500,000 | 5 | 70.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5045-il | 1,000,000 | 9 | 92.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5045-il | 1,000,000 | 5 | 81.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 50,000 | 9 | 25 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 50,000 | 5 | 23.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 100,000 | 9 | 41.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 100,000 | 5 | 40.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 200,000 | 9 | 59.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 200,000 | 5 | 56.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 500,000 | 9 | 81.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 500,000 | 5 | 71 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 1,000,000 | 9 | 96.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 1,000,000 | 5 | 79.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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