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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(usa25-il) USA 25 AIRFOIL | USA-25 airfoil Max thickness 8.3% at 19.9% chord Max camber 5.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(usa27-il) USA 27 AIRFOIL | USA-27 airfoil Max thickness 11.1% at 30% chord Max camber 5.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(usa28-il) USA 28 AIRFOIL | USA-28 airfoil Max thickness 13.2% at 29.9% chord Max camber 3.8% at 49.9% chord | Remove Airfoil details Airfoil plotter |
(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT | University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord | Remove Airfoil details Airfoil plotter |
(usa22-il) USA 22 AIRFOIL | USA-22 airfoil Max thickness 9.1% at 19.9% chord Max camber 4.4% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa25-il,usa27-il,usa28-il,ua79sfm-il,usa22-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa25-il | 50,000 | 9 | 25.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 50,000 | 5 | 35.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 100,000 | 9 | 52.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 100,000 | 5 | 54.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 200,000 | 9 | 74.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 200,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 500,000 | 9 | 102 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 500,000 | 5 | 97.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa25-il | 1,000,000 | 9 | 124.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa25-il | 1,000,000 | 5 | 106.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 50,000 | 9 | 20.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 50,000 | 5 | 35.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 9 | 50.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 5 | 52.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 9 | 69.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 5 | 69 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 9 | 95.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 9 | 117.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 5 | 110.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 50,000 | 9 | 21.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 50,000 | 5 | 31.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 100,000 | 9 | 54.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 100,000 | 5 | 54.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 200,000 | 9 | 75.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 200,000 | 5 | 72.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 500,000 | 9 | 97.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 500,000 | 5 | 87.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa28-il | 1,000,000 | 9 | 114.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa28-il | 1,000,000 | 5 | 88.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 50,000 | 9 | 12.2 at α=17.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 50,000 | 5 | 16.3 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 100,000 | 9 | 41.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 100,000 | 5 | 40.2 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 200,000 | 9 | 82.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 200,000 | 5 | 80 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 500,000 | 9 | 145.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 500,000 | 5 | 142.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sfm-il | 1,000,000 | 9 | 291 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sfm-il | 1,000,000 | 5 | 241.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 50,000 | 9 | 32.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 50,000 | 5 | 37.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 100,000 | 9 | 53.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 100,000 | 5 | 55.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 200,000 | 9 | 73 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 200,000 | 5 | 73.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 500,000 | 9 | 99.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 500,000 | 5 | 96.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa22-il | 1,000,000 | 9 | 119.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa22-il | 1,000,000 | 5 | 112.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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