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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(hq2195-il) HQ 2.1/9.5 AIRFOIL | Quabeck HQ 2.1/9.5 R/C sailplane airfoil Max thickness 9.5% at 35% chord Max camber 2.1% at 55% chord | Remove Airfoil details Airfoil plotter |
(e558-il) EPPLER 558 AIRFOIL | Eppler E558 general aviation airfoil Max thickness 16% at 26.4% chord Max camber 3.8% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(mrc-20-il) MRC-20 | Drela MRC-20 Max thickness 15.6% at 38.2% chord Max camber 2.9% at 48% chord | Remove Airfoil details Airfoil plotter |
(hq1510-il) HQ 1.5/10 AIRFOIL | Quabeck HQ 1.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2 | NACA 0012-64 a=0.8 c(li)=0.2 airfoil Max thickness 11% at 39.9% chord Max camber 1.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hq2195-il,e558-il,mrc-20-il,hq1510-il,naca001264a08cli02-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq2195-il | 50,000 | 9 | 37.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 50,000 | 5 | 37.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 9 | 55.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 100,000 | 5 | 52.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 9 | 74.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 200,000 | 5 | 67.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 9 | 96.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 500,000 | 5 | 79 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 9 | 101 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2195-il | 1,000,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 50,000 | 9 | 9.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 50,000 | 5 | 29.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 100,000 | 9 | 41.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 100,000 | 5 | 50.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 200,000 | 9 | 67.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 200,000 | 5 | 70.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 500,000 | 9 | 100.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 500,000 | 5 | 99.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 9 | 127 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 5 | 120.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 50,000 | 9 | 23.9 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 50,000 | 5 | 29.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 100,000 | 9 | 50.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 100,000 | 5 | 50.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 200,000 | 9 | 73.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 200,000 | 5 | 68.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 500,000 | 9 | 99.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 500,000 | 5 | 86.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mrc-20-il | 1,000,000 | 9 | 114.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mrc-20-il | 1,000,000 | 5 | 100.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1510-il | 50,000 | 9 | 34.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1510-il | 50,000 | 5 | 35.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1510-il | 100,000 | 9 | 51.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1510-il | 100,000 | 5 | 49.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1510-il | 200,000 | 9 | 68.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1510-il | 200,000 | 5 | 61.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1510-il | 500,000 | 9 | 88.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1510-il | 500,000 | 5 | 73.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1510-il | 1,000,000 | 9 | 92.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1510-il | 1,000,000 | 5 | 81 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 50,000 | 9 | 33 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 50,000 | 5 | 32.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 100,000 | 9 | 49.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 100,000 | 5 | 48.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 200,000 | 9 | 66.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 200,000 | 5 | 61.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 500,000 | 9 | 80.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 500,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 1,000,000 | 9 | 77 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 1,000,000 | 5 | 72.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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