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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(cast102-il) CAST 10-2/DOA 2 AIRFOIL | CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord | Remove Airfoil details Airfoil plotter |
(arad13-il) ARA-D 13% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 13% thick propeller airfoil Max thickness 13% at 25% chord Max camber 3.6% at 30% chord | Remove Airfoil details Airfoil plotter |
(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 |
(clarkk-il) CLARK K AIRFOIL | CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(arad6-il) ARA-D 6% AIRFOIL | Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 6% thick propeller airfoil Max thickness 6% at 20% chord Max camber 5% at 45% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (cast102-il,arad13-il,arad10-il,clarkk-il,arad6-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cast102-il | 50,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 5 | 30.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 9 | 45.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 9 | 64 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 5 | 55.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 9 | 85.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 5 | 66.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 9 | 93.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 5 | 75.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 50,000 | 9 | 25.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 50,000 | 5 | 31.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 100,000 | 9 | 41.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 100,000 | 5 | 44.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 200,000 | 9 | 56.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 200,000 | 5 | 58.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 500,000 | 9 | 78.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 500,000 | 5 | 79.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad13-il | 1,000,000 | 9 | 97.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad13-il | 1,000,000 | 5 | 96.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| clarkk-il | 50,000 | 9 | 32.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 9 | 54.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 100,000 | 5 | 54.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 9 | 75.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 200,000 | 5 | 71.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 9 | 102.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 500,000 | 5 | 91.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 9 | 121.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkk-il | 1,000,000 | 5 | 104.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 50,000 | 9 | 46 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 50,000 | 5 | 45.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 100,000 | 9 | 68.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 100,000 | 5 | 66.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 200,000 | 9 | 93 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 200,000 | 5 | 86 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 500,000 | 9 | 122.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 500,000 | 5 | 105.6 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| arad6-il | 1,000,000 | 9 | 139.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| arad6-il | 1,000,000 | 5 | 106 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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