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 | ||
(hq108-il) HQ 1.0/8 AIRFOIL | Quabeck HQ 1.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
(hsnlf213-il) HSNLF(1)-0213 AIRFOIL | NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord Max camber 1.4% at 32.4% chord | Remove Airfoil details Airfoil plotter |
(hq010-il) HQ 0/10 AIRFOIL | Quabeck HQ 0/10 R/C sailplane airfoil Max thickness 10% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (hq108-il,hsnlf213-il,hq010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq108-il | 50,000 | 9 | 33.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq108-il | 50,000 | 5 | 33.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq108-il | 100,000 | 9 | 48 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq108-il | 100,000 | 5 | 44.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq108-il | 200,000 | 9 | 62.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq108-il | 200,000 | 5 | 54.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq108-il | 500,000 | 9 | 78.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq108-il | 500,000 | 5 | 63.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq108-il | 1,000,000 | 9 | 85 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq108-il | 1,000,000 | 5 | 72.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 50,000 | 9 | 28.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 50,000 | 5 | 27.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 100,000 | 9 | 46 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 100,000 | 5 | 37.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 200,000 | 9 | 53.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 200,000 | 5 | 49.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 500,000 | 9 | 70.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 500,000 | 5 | 59.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 1,000,000 | 9 | 78.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 1,000,000 | 5 | 67.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 50,000 | 9 | 28 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 50,000 | 5 | 27.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 100,000 | 9 | 39.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 100,000 | 5 | 36 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 200,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 200,000 | 5 | 41.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 500,000 | 9 | 54.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 500,000 | 5 | 56.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq010-il | 1,000,000 | 9 | 71 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq010-il | 1,000,000 | 5 | 70.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||