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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(vr15-il) BOEING-VERTOL VR-15 AIRFOIL | Boeing-Vertol/Dadone VR-15 transonic rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.3% at 20% chord | Remove Airfoil details Airfoil plotter |
(sd7003-il) SD7003-085-88 | Selig/Donovan SD7003 low Reynolds number airfoil Max thickness 8.5% at 24.4% chord Max camber 1.2% at 38.3% chord | Remove Airfoil details Airfoil plotter |
(sd6080-il) SD6080 (9.2%) | Selig/Donovan SD6080 low Reynolds number airfoil Max thickness 9.2% at 30.9% chord Max camber 3.2% at 44.7% chord | Remove Airfoil details Airfoil plotter |
(mh33-il) MH33 | Martin Hepperle MH 33 for F3E and F3B Max thickness 7.3% at 29.3% chord Max camber 1.1% at 43.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (vr15-il,sd7003-il,sd6080-il,mh33-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr15-il | 50,000 | 9 | 28.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 50,000 | 5 | 27.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 100,000 | 9 | 38.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 100,000 | 5 | 39 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 200,000 | 9 | 49.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 200,000 | 5 | 52 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 500,000 | 9 | 70.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 500,000 | 5 | 69.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 1,000,000 | 9 | 85.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 1,000,000 | 5 | 81.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7003-il | 50,000 | 9 | 29.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7003-il | 50,000 | 5 | 32.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7003-il | 100,000 | 9 | 43.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7003-il | 100,000 | 5 | 45.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7003-il | 200,000 | 9 | 58.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7003-il | 200,000 | 5 | 58 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7003-il | 500,000 | 9 | 78.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7003-il | 500,000 | 5 | 76 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7003-il | 1,000,000 | 9 | 93.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7003-il | 1,000,000 | 5 | 89.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6080-il | 50,000 | 9 | 36.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6080-il | 50,000 | 5 | 39.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6080-il | 100,000 | 9 | 59.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6080-il | 100,000 | 5 | 60.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6080-il | 200,000 | 9 | 83.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6080-il | 200,000 | 5 | 80.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6080-il | 500,000 | 9 | 115.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6080-il | 500,000 | 5 | 104.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6080-il | 1,000,000 | 9 | 137.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6080-il | 1,000,000 | 5 | 119.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 50,000 | 9 | 32.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 50,000 | 5 | 31.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 100,000 | 9 | 46.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 100,000 | 5 | 42.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 200,000 | 9 | 59.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 200,000 | 5 | 51.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 500,000 | 9 | 72.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 500,000 | 5 | 64.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh33-il | 1,000,000 | 9 | 81.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh33-il | 1,000,000 | 5 | 74.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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