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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(hq09-il) HQ 0/9 AIRFOIL | Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL | Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
(vr11x-il) BOEING-VERTOL VR-11X AIRFOIL | Boeing-Vertol/NASA/Dadone VR-11X transonic rotorcraft airfoil Max thickness 11% at 40% chord Max camber 2.4% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq09-il,v43015-il,vr11x-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq09-il | 50,000 | 9 | 27.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 50,000 | 5 | 26 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 9 | 36.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 5 | 33.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 9 | 46.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 5 | 38.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 9 | 51.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 5 | 53.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 9 | 64.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 9 | 30.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 50,000 | 5 | 29.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 9 | 41 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 100,000 | 5 | 39.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 9 | 55.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 200,000 | 5 | 51.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 9 | 71.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 500,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 9 | 92.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr11x-il | 1,000,000 | 5 | 89.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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