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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(atr72sm-il) Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) | ATR 72 wing airfoil (from NTSB report) Max thickness 14.5% at 25.4% chord Max camber 2.9% at 21.4% 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 |
(ah82150a-il) AH 82-150 A | Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% 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 |
(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 |
(ah80140-il) AH 80-140 | Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord Max camber 4.4% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(ah21-7-il) AH21 7% version (Andrew Hollom) | Andrew Hollom AH 21 airfoil (7% version) Max thickness 9% at 34.9% chord Max camber 2.3% at 54.8% chord | Remove Airfoil details Airfoil plotter |
(ag45c03-il) AG45c -03f | Drela AG45c -03f airfoil Max thickness 6.9% at 23.5% chord Max camber 2% at 31.7% chord | Remove Airfoil details Airfoil plotter |
(ah6407-il) AH-6-40-7 AIRFOIL | Althaus AH 6-407 airfoil Max thickness 6.9% at 20% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(august160-il) AUGUST 160 | AUGUST 160 airfoil Max thickness 16% at 25% chord Max camber 5.4% at 25% chord | Remove Airfoil details Airfoil plotter |
(amsoil1-il) RUTAN CANARD AIRFOIL | Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (atr72sm-il,ah85l120-il,ah82150a-il,ah93k131-il,apex16-il,ah80140-il,ah21-7-il,ag45c03-il,ah6407-il,august160-il,amsoil1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| atr72sm-il | 50,000 | 9 | 20.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 50,000 | 5 | 25.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 100,000 | 9 | 33.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 100,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 200,000 | 9 | 48.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 200,000 | 5 | 55.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 500,000 | 9 | 77.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 500,000 | 5 | 81.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 1,000,000 | 9 | 104.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 1,000,000 | 5 | 105.2 at α=9.25° | 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 | |
| ah82150a-il | 50,000 | 9 | 17.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 50,000 | 5 | 20.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 5 | 41.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 9 | 72.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 5 | 73.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 9 | 108.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 5 | 107.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 9 | 137.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 5 | 129.9 at α=4.5° | 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 | |
| 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 | |
| ah80140-il | 50,000 | 9 | 5.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 50,000 | 5 | 14.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 9 | 22.5 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 5 | 35.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 9 | 70.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 5 | 74.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 9 | 116.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 5 | 113.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 9 | 149.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 5 | 139 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 50,000 | 9 | 35.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 100,000 | 5 | 51.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 9 | 78.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 200,000 | 5 | 69.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 9 | 111.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 500,000 | 5 | 82.9 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-7-il | 1,000,000 | 5 | 84.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 50,000 | 9 | 29.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 50,000 | 5 | 34.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 100,000 | 9 | 46 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 100,000 | 5 | 47.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 200,000 | 9 | 62.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 200,000 | 5 | 61 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 500,000 | 9 | 83 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 500,000 | 5 | 78.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 1,000,000 | 9 | 97.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 1,000,000 | 5 | 91.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 50,000 | 9 | 41.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 50,000 | 5 | 46.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 9 | 67.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 100,000 | 5 | 67.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 9 | 91.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 200,000 | 5 | 85.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 9 | 119.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 500,000 | 5 | 104 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 9 | 131.3 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah6407-il | 1,000,000 | 5 | 121.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 50,000 | 9 | 4.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 50,000 | 5 | 17.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 100,000 | 9 | 20.8 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 100,000 | 5 | 34.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 200,000 | 9 | 42.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 200,000 | 5 | 56.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 500,000 | 9 | 82.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 500,000 | 5 | 90.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| august160-il | 1,000,000 | 9 | 117.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| august160-il | 1,000,000 | 5 | 120.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 50,000 | 9 | 33 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 50,000 | 5 | 31.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 9 | 48.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 100,000 | 5 | 46.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 9 | 67.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 200,000 | 5 | 59.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 9 | 86.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 500,000 | 5 | 68.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 9 | 93 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| amsoil1-il | 1,000,000 | 5 | 81.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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