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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(arad10-il) ARA-D 10% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 10% thick propeller airfoil Max thickness 10% at 25% chord Max camber 4% at 35% chord | Remove Airfoil details Airfoil plotter |
(ames03-il) NASA/AMES A-03 AIRFOIL | NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord | Remove Airfoil details Airfoil plotter |
(ah79100b-il) AH 79-100 B AIRFOIL | Althaus AH 79-100B airfoil Max thickness 10% at 30.9% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(ames01-il) NASA/AMES A-01 AIRFOIL | NASA/AMES/Hicks A-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (arad10-il,ames03-il,ah79100b-il,ames01-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| arad10-il | 50,000 | 9 | 34.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad10-il | 50,000 | 5 | 36.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad10-il | 100,000 | 9 | 51.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad10-il | 100,000 | 5 | 49.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad10-il | 200,000 | 9 | 66.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad10-il | 200,000 | 5 | 61.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad10-il | 500,000 | 9 | 82.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad10-il | 500,000 | 5 | 82.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad10-il | 1,000,000 | 9 | 100.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad10-il | 1,000,000 | 5 | 98.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 50,000 | 9 | 27.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 50,000 | 5 | 27.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 100,000 | 9 | 34.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 100,000 | 5 | 39.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 200,000 | 9 | 50.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 200,000 | 5 | 53.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 500,000 | 9 | 72.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 500,000 | 5 | 70.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames03-il | 1,000,000 | 9 | 87.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames03-il | 1,000,000 | 5 | 83.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 50,000 | 9 | 32.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 50,000 | 5 | 32.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 9 | 65.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 100,000 | 5 | 68.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 9 | 100 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 200,000 | 5 | 101 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 9 | 148.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 500,000 | 5 | 139.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 9 | 183.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah79100b-il | 1,000,000 | 5 | 153.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 50,000 | 9 | 25.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 50,000 | 5 | 27.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 100,000 | 9 | 35 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 100,000 | 5 | 40.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 200,000 | 9 | 53.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 200,000 | 5 | 55.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 500,000 | 9 | 76.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 500,000 | 5 | 74.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 1,000,000 | 9 | 93.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 1,000,000 | 5 | 88.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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