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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(raf25-il) RAF 25 AIRFOIL | RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% 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 |
(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 |
(n64008a-il) NACA 64-008A AIRFOIL | NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ua79sff-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT | University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP Max thickness 8.7% at 73.1% chord Max camber 3.4% at 78.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf25-il,ua79sfm-il,usa27-il,n64008a-il,ua79sff-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf25-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 50,000 | 5 | 30.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 9 | 43.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 100,000 | 5 | 40.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 9 | 56.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 200,000 | 5 | 47.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 9 | 68.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 500,000 | 5 | 55.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 9 | 72.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf25-il | 1,000,000 | 5 | 68.1 at α=5° | 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 | |
| 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 | |
| n64008a-il | 50,000 | 9 | 19.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 50,000 | 5 | 23.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 9 | 32.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 100,000 | 5 | 30.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 9 | 41 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 200,000 | 5 | 35 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 9 | 46.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 500,000 | 5 | 44.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 9 | 49.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n64008a-il | 1,000,000 | 5 | 59.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 50,000 | 9 | 3.4 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 50,000 | 5 | 3.5 at α=19.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 9 | 3.6 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 5 | 4.1 at α=18.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 9 | 3.8 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 5 | 5.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 9 | 6.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 5 | 25.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 5 | 62 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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