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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(goe624-il) GOE 624 AIRFOIL | Gottingen 624 airfoil Max thickness 16% at 30% chord Max camber 5.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(b29root-il) B-29 ROOT AIRFOIL | Boeing B-29 root airfoil Max thickness 22% at 30.2% chord Max camber 1.7% at 30.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe624-il,b29root-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe624-il | 50,000 | 9 | 5.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe624-il | 50,000 | 5 | 22.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe624-il | 100,000 | 9 | 39.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe624-il | 100,000 | 5 | 50.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe624-il | 200,000 | 9 | 69.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe624-il | 200,000 | 5 | 69.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe624-il | 500,000 | 9 | 99.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe624-il | 500,000 | 5 | 97.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe624-il | 1,000,000 | 9 | 126.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe624-il | 1,000,000 | 5 | 120.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 50,000 | 9 | 2.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 50,000 | 5 | 8.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 100,000 | 9 | 13.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 100,000 | 5 | 34.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 200,000 | 9 | 58.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 200,000 | 5 | 52.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 500,000 | 9 | 77.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 500,000 | 5 | 68.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29root-il | 1,000,000 | 9 | 90.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29root-il | 1,000,000 | 5 | 83.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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