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 | ||
(coanda2-il) Coanda 2 | Coanda 2 airfoil Max thickness 6% at 30% chord Max camber 2.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(hq208-il) HQ 2.0/8 AIRFOIL | Quabeck HQ 2.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED) | Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord Max camber 4.5% at 42% chord | Remove Airfoil details Airfoil plotter |
(coanda3-il) Coanda 3 | Coanda 3 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (coanda2-il,hq208-il,hq17-il,coanda3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| coanda2-il | 50,000 | 9 | 37.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 50,000 | 5 | 37.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 100,000 | 9 | 53.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 100,000 | 5 | 48 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 200,000 | 9 | 64.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 200,000 | 5 | 49.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 500,000 | 9 | 62.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 500,000 | 5 | 52.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda2-il | 1,000,000 | 9 | 58.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda2-il | 1,000,000 | 5 | 58.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 50,000 | 9 | 37.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 50,000 | 5 | 38.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 100,000 | 9 | 55.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 100,000 | 5 | 53.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 200,000 | 9 | 74.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 200,000 | 5 | 68.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 500,000 | 9 | 98.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 500,000 | 5 | 83.4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq208-il | 1,000,000 | 9 | 112.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq208-il | 1,000,000 | 5 | 84.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 50,000 | 9 | 22.5 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 50,000 | 5 | 18.3 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 100,000 | 9 | 34.2 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 100,000 | 5 | 32.5 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 200,000 | 9 | 68.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 200,000 | 5 | 66.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 500,000 | 9 | 113.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 500,000 | 5 | 103.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq17-il | 1,000,000 | 9 | 139.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq17-il | 1,000,000 | 5 | 122.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 50,000 | 9 | 37.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 50,000 | 5 | 37.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 100,000 | 9 | 55.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 100,000 | 5 | 52.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 200,000 | 9 | 75.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 200,000 | 5 | 67.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 500,000 | 9 | 94.6 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 500,000 | 5 | 76 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 1,000,000 | 9 | 89 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 1,000,000 | 5 | 80.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||