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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(ag455ct02r-il) AG455ct -02f rot. | Drela AG455ct -02f airfoil Max thickness 6.5% at 23.3% chord Max camber 1.8% at 33.1% chord | Remove Airfoil details Airfoil plotter |
(ah85l120-il) AH 85-L-120/17 | Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ah95160-il) AH 95-160 | Althaus AH 95-160 airfoil Max thickness 16% at 38.9% chord Max camber 5.6% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(ah93k131-il) AH 93-K-131/15 | Althaus AH 93-K-131/15 airfoil for use with flaps (K) Max thickness 13.1% at 41.3% chord Max camber 3.6% at 41.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag455ct02r-il,ah85l120-il,ah95160-il,ah93k131-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag455ct02r-il | 50,000 | 9 | 30.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 50,000 | 5 | 34 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 100,000 | 9 | 44.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 100,000 | 5 | 46 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 200,000 | 9 | 59.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 200,000 | 5 | 58.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 500,000 | 9 | 78.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 500,000 | 5 | 75.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag455ct02r-il | 1,000,000 | 9 | 92.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag455ct02r-il | 1,000,000 | 5 | 88.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 50,000 | 9 | 21.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 50,000 | 5 | 27.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 9 | 37.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 100,000 | 5 | 29.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 200,000 | 5 | 35 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 9 | 48.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 500,000 | 5 | 43.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 9 | 55.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah85l120-il | 1,000,000 | 5 | 52 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 50,000 | 9 | 5.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 50,000 | 5 | 12.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 9 | 23.9 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 100,000 | 5 | 24.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 9 | 65.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 200,000 | 5 | 73.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 9 | 130.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 500,000 | 5 | 128.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 9 | 173.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah95160-il | 1,000,000 | 5 | 163.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k131-il | 50,000 | 9 | 25 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k131-il | 50,000 | 5 | 22 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k131-il | 100,000 | 9 | 42.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k131-il | 100,000 | 5 | 40.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k131-il | 200,000 | 9 | 76 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k131-il | 200,000 | 5 | 74.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k131-il | 500,000 | 9 | 115.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k131-il | 500,000 | 5 | 105.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93k131-il | 1,000,000 | 9 | 138.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93k131-il | 1,000,000 | 5 | 111.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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