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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(hq3014-il) HQ 3.0/14 AIRFOIL | Quabeck HQ 3.0/14 R/C sailplane airfoil Max thickness 14% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq359-il) HQ 3.5/9 AIRFOIL | Quabeck HQ 3.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL | NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord | Remove Airfoil details Airfoil plotter |
(nlf1015-il) NASA NLF1015 | NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil Max thickness 15% at 39.8% chord Max camber 4.3% at 62.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq3014-il,hq359-il,nlf0215f-il,nlf1015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq3014-il | 50,000 | 9 | 30.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 50,000 | 5 | 33 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 100,000 | 9 | 54.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 100,000 | 5 | 53.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 200,000 | 9 | 77.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 200,000 | 5 | 70.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 500,000 | 9 | 99.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 500,000 | 5 | 85.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 1,000,000 | 9 | 113.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 1,000,000 | 5 | 96.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq359-il | 50,000 | 9 | 39.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq359-il | 50,000 | 5 | 42 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq359-il | 100,000 | 9 | 63.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq359-il | 100,000 | 5 | 62.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq359-il | 200,000 | 9 | 88.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq359-il | 200,000 | 5 | 82.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq359-il | 500,000 | 9 | 121.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq359-il | 500,000 | 5 | 101.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq359-il | 1,000,000 | 9 | 140.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq359-il | 1,000,000 | 5 | 105.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 50,000 | 9 | 25.9 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 50,000 | 5 | 20.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 100,000 | 9 | 46.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 100,000 | 5 | 49.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 200,000 | 9 | 76.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 200,000 | 5 | 76.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 500,000 | 9 | 110.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 500,000 | 5 | 108.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 1,000,000 | 9 | 139.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 1,000,000 | 5 | 131.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 50,000 | 9 | 25.8 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 50,000 | 5 | 21.9 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 100,000 | 9 | 40.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 100,000 | 5 | 38.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 200,000 | 9 | 75.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 200,000 | 5 | 77.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 500,000 | 9 | 130.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 500,000 | 5 | 125.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf1015-il | 1,000,000 | 9 | 167.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf1015-il | 1,000,000 | 5 | 154.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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