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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(e1212mod-il) EPPLER E1212MOD AIRFOIL | Eppler E1212 general aviation airfoil (as modified for use as Quickie wing airfoil) Max thickness 17.7% at 20.1% chord Max camber 2.6% at 35.1% chord | Remove Airfoil details Airfoil plotter |
(p51dtip-il) P-51D TIP (BL215) AIRFOIL | P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord | Remove Airfoil details Airfoil plotter |
(b29tip-il) B-29 TIP AIRFOIL | Boeing B-29 tip airfoil Max thickness 9% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(e67-il) EPPLER 67 AIRFOIL | Eppler E67 low Reynolds number airfoil Max thickness 11.6% at 32.6% chord Max camber 3.7% at 51.6% chord | Remove Airfoil details Airfoil plotter |
(joukowsk0009-jf) Joukovsky f=0% t=9% | Joukowski 9% symmetrical airfoil Max thickness 9% at 25.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e1212mod-il,p51dtip-il,b29tip-il,e67-il,joukowsk0009-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1212mod-il | 50,000 | 9 | 5.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 50,000 | 5 | 20.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 100,000 | 9 | 28 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 100,000 | 5 | 39.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 200,000 | 9 | 51.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 200,000 | 5 | 57.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 500,000 | 9 | 81.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 500,000 | 5 | 84.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212mod-il | 1,000,000 | 9 | 108.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212mod-il | 1,000,000 | 5 | 107.6 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 9 | 22.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 5 | 23.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 9 | 40.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 5 | 35.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 9 | 54.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 5 | 49.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 9 | 74.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 5 | 63.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 9 | 89.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 5 | 68.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 50,000 | 9 | 34.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 50,000 | 5 | 34.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 100,000 | 5 | 50.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 9 | 68.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 200,000 | 5 | 66.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 9 | 91.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 500,000 | 5 | 84.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 9 | 106.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b29tip-il | 1,000,000 | 5 | 90 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 50,000 | 9 | 37.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 50,000 | 5 | 36.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 100,000 | 9 | 60.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 100,000 | 5 | 60.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 200,000 | 9 | 86.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 200,000 | 5 | 82.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 500,000 | 9 | 121.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 500,000 | 5 | 107.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 9 | 144.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e67-il | 1,000,000 | 5 | 117.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 50,000 | 9 | 23.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 50,000 | 5 | 25.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 100,000 | 9 | 33.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 100,000 | 5 | 34.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 200,000 | 9 | 44.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 200,000 | 5 | 44.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 500,000 | 9 | 58.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 500,000 | 5 | 60.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| joukowsk0009-jf | 1,000,000 | 9 | 72.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| joukowsk0009-jf | 1,000,000 | 5 | 74.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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