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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(ah83150q-il) AH 83-150 Q | Althaus AH 83-150 Q airfoil Max thickness 15% at 40.2% chord Max camber 4.1% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(dsma523b-il) DSMA-523B AIRFOIL | McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge Max thickness 11% at 36% chord Max camber 2.4% at 82% chord | Remove Airfoil details Airfoil plotter |
(fx68h120-il) FX 68-H-120 | Wortmann FX 68-H-120 airfoil Max thickness 11.8% at 25% chord Max camber 2.3% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(s1014-il) S1014 | Selig S1014 HPV airfoil Max thickness 16.5% at 42.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e1233-il) EPPLER 1233 AIRFOIL | Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord Max camber 4.4% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah83150q-il,dsma523b-il,fx68h120-il,s1014-il,e1233-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah83150q-il | 50,000 | 9 | 6.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 50,000 | 5 | 15.9 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 100,000 | 9 | 39.6 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 100,000 | 5 | 35.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 200,000 | 9 | 73.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 200,000 | 5 | 71.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 500,000 | 9 | 109.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 500,000 | 5 | 102.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah83150q-il | 1,000,000 | 9 | 134.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah83150q-il | 1,000,000 | 5 | 122.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 50,000 | 9 | 20.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 50,000 | 5 | 20.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 100,000 | 9 | 23.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 100,000 | 5 | 27.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 200,000 | 9 | 29.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 200,000 | 5 | 39.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 500,000 | 9 | 49.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 500,000 | 5 | 60 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dsma523b-il | 1,000,000 | 9 | 73.2 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dsma523b-il | 1,000,000 | 5 | 77.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 50,000 | 5 | 29.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 100,000 | 9 | 40.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 100,000 | 5 | 41 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 200,000 | 9 | 54.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 200,000 | 5 | 54.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 500,000 | 9 | 74.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 500,000 | 5 | 73.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 1,000,000 | 9 | 91.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 1,000,000 | 5 | 88.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 50,000 | 9 | 27 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 50,000 | 5 | 20.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 100,000 | 9 | 38.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 100,000 | 5 | 23.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 200,000 | 9 | 33.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 200,000 | 5 | 30.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 500,000 | 9 | 45.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 500,000 | 5 | 42 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1014-il | 1,000,000 | 9 | 54.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1014-il | 1,000,000 | 5 | 52.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 9 | 15.7 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 5 | 21.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 9 | 34 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 5 | 41.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 9 | 56.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 5 | 58.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 9 | 81 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 5 | 81.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 9 | 104.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 5 | 103.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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