Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(lwk79100-il) LWK 79-100 | LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(hq3011-il) HQ 3.0/11 AIRFOIL | Quabeck HQ 3.0/11 R/C sailplane airfoil Max thickness 11% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3513-il) HQ 3.5/13 AIRFOIL | Quabeck HQ 3.5/13 R/C sailplane airfoil Max thickness 13% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3512-il) HQ 3.5/12 AIRFOIL | Quabeck HQ 3.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (lwk79100-il,hq3011-il,hq3513-il,hq3512-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lwk79100-il | 50,000 | 9 | 25.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 9 | 37.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 100,000 | 5 | 35.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 9 | 47.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 200,000 | 5 | 44.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 9 | 59.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 500,000 | 5 | 60.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 9 | 72.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lwk79100-il | 1,000,000 | 5 | 74.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 50,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 100,000 | 9 | 58.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 100,000 | 5 | 57.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 200,000 | 9 | 81.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 200,000 | 5 | 75.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 500,000 | 9 | 111.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 500,000 | 5 | 92.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 1,000,000 | 9 | 124.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 1,000,000 | 5 | 101.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3513-il | 50,000 | 9 | 30.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3513-il | 50,000 | 5 | 35.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3513-il | 100,000 | 9 | 56.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3513-il | 100,000 | 5 | 56 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3513-il | 200,000 | 9 | 81.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3513-il | 200,000 | 5 | 75.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3513-il | 500,000 | 9 | 105.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3513-il | 500,000 | 5 | 88.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3513-il | 1,000,000 | 9 | 119.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3513-il | 1,000,000 | 5 | 101.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3512-il | 50,000 | 9 | 33.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3512-il | 50,000 | 5 | 37.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3512-il | 100,000 | 9 | 58.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3512-il | 100,000 | 5 | 57.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3512-il | 200,000 | 9 | 83.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3512-il | 200,000 | 5 | 77.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3512-il | 500,000 | 9 | 112.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3512-il | 500,000 | 5 | 90.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3512-il | 1,000,000 | 9 | 122 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3512-il | 1,000,000 | 5 | 102.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||