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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(fx75193-il) WORTMANN FX 75-193 | Wortmann FX 75-193 airfoil Max thickness 19.3% at 40.2% chord Max camber 3.7% at 69.1% chord | Remove Airfoil details Airfoil plotter |
(goe15-il) GOE 15 AIRFOIL | Gottingen 15 airfoil Max thickness 9% at 29.8% chord Max camber 7.8% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe142-il) GOE 142 (MVA H.19) AIRFOIL | Gottingen 142 (MVA H.19) airfoil Max thickness 6.2% at 24.9% chord Max camber 3.8% at 34.9% 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 |
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Polars for (fx75193-il,goe15-il,goe142-il,arad10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx75193-il | 50,000 | 9 | 4.2 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 50,000 | 5 | 11.7 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 9 | 23.4 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 100,000 | 5 | 22.9 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 9 | 43.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 200,000 | 5 | 44.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 9 | 91.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 500,000 | 5 | 93.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 9 | 122.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75193-il | 1,000,000 | 5 | 120.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15-il | 50,000 | 9 | 8.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15-il | 50,000 | 5 | 31.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15-il | 100,000 | 9 | 46.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15-il | 100,000 | 5 | 53.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15-il | 200,000 | 9 | 70.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15-il | 200,000 | 5 | 72.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15-il | 500,000 | 9 | 126.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15-il | 500,000 | 5 | 94.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe15-il | 1,000,000 | 9 | 128.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe15-il | 1,000,000 | 5 | 115.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 50,000 | 9 | 36.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 50,000 | 5 | 41 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 100,000 | 9 | 55.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 100,000 | 5 | 56.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 200,000 | 9 | 74.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 200,000 | 5 | 72.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 500,000 | 9 | 99 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 500,000 | 5 | 94.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 1,000,000 | 9 | 118.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 1,000,000 | 5 | 111.4 at α=5° | 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 | |
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