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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(e178-il) E178 (8.69%) | Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord | Remove Airfoil details Airfoil plotter |
(e201-il) E201 (11.88%) | Eppler E201 low Reynolds number airfoil Max thickness 11.9% at 30.8% chord Max camber 2.6% at 49.4% chord | Remove Airfoil details Airfoil plotter |
(arad20-il) ARA-D 20% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 20% thick propeller airfoil Max thickness 20% at 25% chord Max camber 3.8% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e178-il,e201-il,arad20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e178-il | 50,000 | 9 | 36.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 50,000 | 5 | 37.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 100,000 | 9 | 56.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 100,000 | 5 | 55.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 200,000 | 9 | 77.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 200,000 | 5 | 73.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 500,000 | 9 | 105 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 500,000 | 5 | 95.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 1,000,000 | 9 | 125.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 1,000,000 | 5 | 108.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 50,000 | 9 | 34 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 50,000 | 5 | 33.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 100,000 | 9 | 56.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 100,000 | 5 | 57 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 200,000 | 9 | 80.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 200,000 | 5 | 78.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 500,000 | 9 | 112 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 500,000 | 5 | 104.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e201-il | 1,000,000 | 9 | 135.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e201-il | 1,000,000 | 5 | 122.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 50,000 | 9 | 9.7 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 50,000 | 5 | 18.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 100,000 | 9 | 24.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 100,000 | 5 | 38.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 200,000 | 9 | 52 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 200,000 | 5 | 56.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 500,000 | 9 | 79.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 500,000 | 5 | 80.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad20-il | 1,000,000 | 9 | 101.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad20-il | 1,000,000 | 5 | 98.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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