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 |
(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 |
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6 | HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% 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 (atr72sm-il,ah95160-il,cp-080-050-gn,ah93k131-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 | |
| 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 | |
| cp-080-050-gn | 50,000 | 9 | 25.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 50,000 | 5 | 24.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 50,000 | 1 | 22 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 9 | 30 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 5 | 29.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 1 | 30.1 at α=8° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 9 | 33.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 5 | 34.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 1 | 37.7 at α=7.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 9 | 41.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 5 | 44.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 1 | 51.4 at α=8° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 9 | 50.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 5 | 57.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 1 | 64.2 at α=8.5° | Mach=0 Ncrit=1 | 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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