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 | ||
(cast102-il) CAST 10-2/DOA 2 AIRFOIL | CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord | Remove Airfoil details Airfoil plotter |
(hq1511-il) HQ 1.5/11 AIRFOIL | Quabeck HQ 1.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(b707c-il) BOEING 707 .40 SPAN AIRFOIL | Boeing Commercial Airplane Company model 707 airfoils Max thickness 9.6% at 30% chord Max camber 1.9% at 15% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (cast102-il,hq1511-il,b707c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cast102-il | 50,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 50,000 | 5 | 30.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 9 | 45.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 100,000 | 5 | 43 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 9 | 64 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 200,000 | 5 | 55.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 9 | 85.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 500,000 | 5 | 66.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 9 | 93.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cast102-il | 1,000,000 | 5 | 75.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 50,000 | 9 | 33.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 50,000 | 5 | 34.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 100,000 | 9 | 50.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 100,000 | 5 | 48.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 200,000 | 9 | 67.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 200,000 | 5 | 59.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 500,000 | 9 | 82.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 500,000 | 5 | 74 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1511-il | 1,000,000 | 9 | 94.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1511-il | 1,000,000 | 5 | 82.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707c-il | 50,000 | 9 | 33.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707c-il | 50,000 | 5 | 30.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707c-il | 100,000 | 9 | 42.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707c-il | 100,000 | 5 | 34.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707c-il | 200,000 | 9 | 43.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707c-il | 200,000 | 5 | 43.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707c-il | 500,000 | 9 | 61.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707c-il | 500,000 | 5 | 58.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707c-il | 1,000,000 | 9 | 73.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707c-il | 1,000,000 | 5 | 61.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||