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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(ah83159-il) AH 83-159 | Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord | Remove Airfoil details Airfoil plotter |
(ah81k144wfklappe-il) AH 81-K-144 W-F KLAPPE | Althaus AH 81-K-144 W-F KLAPPE airfoil for use with flaps (K) Max thickness 22% at 17% chord Max camber 1.1% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(ah88k136-il) AH 88-K-136/16 | Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah83159-il,ah81k144wfklappe-il,ah88k136-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah83159-il | 50,000 | 9 | 17.1 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 50,000 | 5 | 15.5 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 100,000 | 9 | 31.4 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 100,000 | 5 | 29 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 200,000 | 9 | 64.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 200,000 | 5 | 63.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 500,000 | 9 | 106.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 500,000 | 5 | 105.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83159-il | 1,000,000 | 9 | 136.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83159-il | 1,000,000 | 5 | 133.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 50,000 | 9 | 4.2 at α=-2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 50,000 | 5 | 2.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 100,000 | 9 | 3.8 at α=-1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 100,000 | 5 | 10 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 200,000 | 9 | 10.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 200,000 | 5 | 35.4 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 500,000 | 9 | 68.9 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 500,000 | 5 | 66.7 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 1,000,000 | 9 | 89.7 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah81k144wfklappe-il | 1,000,000 | 5 | 68.5 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 50,000 | 9 | 21.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 50,000 | 5 | 21.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 100,000 | 9 | 40.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 100,000 | 5 | 38.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 200,000 | 9 | 73.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 200,000 | 5 | 72.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 500,000 | 9 | 113.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 500,000 | 5 | 87.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 1,000,000 | 9 | 113.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 1,000,000 | 5 | 95.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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