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 | ||
(hq2012-il) HQ 2.0/12 AIRFOIL | Quabeck HQ 2.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2% at 50% chord | Remove Airfoil details Airfoil plotter |
(bw3-il) Bergey BW-3 (smoothed) | Bergey BW-3 wind turbine airfoil (smoothed) Max thickness 5% at 7.4% chord Max camber 5.7% at 45.4% chord | Remove Airfoil details Airfoil plotter |
(ht22-il) HT22 | Drela HT22 airfoil Max thickness 5.1% at 19.1% chord Max camber 1.1% at 22.7% chord | Remove Airfoil details Airfoil plotter |
(ht23-il) HT23 | Drela HT23 airfoil Max thickness 6.5% at 20.8% chord Max camber 1.1% at 22.6% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (hq2012-il,bw3-il,ht22-il,ht23-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq2012-il | 50,000 | 9 | 33.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2012-il | 50,000 | 5 | 34.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2012-il | 100,000 | 9 | 52.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2012-il | 100,000 | 5 | 51.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2012-il | 200,000 | 9 | 72.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2012-il | 200,000 | 5 | 65.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2012-il | 500,000 | 9 | 90.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2012-il | 500,000 | 5 | 79.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2012-il | 1,000,000 | 9 | 100.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2012-il | 1,000,000 | 5 | 88.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 50,000 | 9 | 46.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 50,000 | 5 | 46 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 100,000 | 9 | 67.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 100,000 | 5 | 58.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 200,000 | 9 | 74.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 200,000 | 5 | 68.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 500,000 | 9 | 88.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 500,000 | 5 | 79.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bw3-il | 1,000,000 | 9 | 98.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bw3-il | 1,000,000 | 5 | 89.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 50,000 | 9 | 25.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 50,000 | 5 | 27.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 100,000 | 9 | 35 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 100,000 | 5 | 36.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 200,000 | 9 | 46 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 200,000 | 5 | 46.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 500,000 | 9 | 60.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 500,000 | 5 | 63.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 1,000,000 | 9 | 75.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 1,000,000 | 5 | 78.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 50,000 | 9 | 24.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 50,000 | 5 | 29 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 9 | 37.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 5 | 39.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 9 | 50.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 5 | 50.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 9 | 67.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 5 | 65.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 9 | 79.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 5 | 79.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||