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 | ||
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL | Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(nacacyh-il) NACA CYH | NACA CYH airfoil Max thickness 11.7% at 30% chord Max camber 2.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(r140sm-il) R140 12.04% (smoothed) | R140 Quickee 500 airfoil (smoothed) Max thickness 12% at 39.3% chord Max camber 0.4% at 39.3% chord | Remove Airfoil details Airfoil plotter |
(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL | NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord | Remove Airfoil details Airfoil plotter |
(nacam18-il) NACA M18 | NACA M18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(npl9615-il) NPL 9615 AIRFOIL | NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (r1082-il,nacacyh-il,r140sm-il,nlf0215f-il,nacam18-il,npl9615-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r1082-il | 50,000 | 9 | 4.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 50,000 | 5 | 12.1 at α=14.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 100,000 | 9 | 25.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 100,000 | 5 | 21.5 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 200,000 | 9 | 60.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 200,000 | 5 | 61.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 500,000 | 9 | 105.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 500,000 | 5 | 102.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 1,000,000 | 9 | 136.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 1,000,000 | 5 | 127.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 50,000 | 9 | 25.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 50,000 | 5 | 33.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 9 | 47.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 5 | 49.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 9 | 65.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 5 | 64.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 9 | 90.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 9 | 110.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 5 | 101 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 50,000 | 9 | 22.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 50,000 | 5 | 29.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 100,000 | 9 | 43 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 100,000 | 5 | 41.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 200,000 | 9 | 53.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 200,000 | 5 | 46.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 500,000 | 9 | 62 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 500,000 | 5 | 53.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r140sm-il | 1,000,000 | 9 | 71.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r140sm-il | 1,000,000 | 5 | 59.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 50,000 | 9 | 25.9 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 50,000 | 5 | 20.8 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 100,000 | 9 | 46.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 100,000 | 5 | 49.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 200,000 | 9 | 76.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 200,000 | 5 | 76.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 500,000 | 9 | 110.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 500,000 | 5 | 108.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlf0215f-il | 1,000,000 | 9 | 139.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlf0215f-il | 1,000,000 | 5 | 131.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 50,000 | 9 | 10.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 50,000 | 5 | 26.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 100,000 | 9 | 47.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 100,000 | 5 | 50.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 200,000 | 9 | 71.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 200,000 | 5 | 72.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 500,000 | 9 | 102.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 500,000 | 5 | 99.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam18-il | 1,000,000 | 9 | 125.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam18-il | 1,000,000 | 5 | 114 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 9 | 29 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 5 | 30.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 9 | 43.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 5 | 42.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 9 | 56.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 9 | 70.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 5 | 68.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 9 | 84.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 5 | 77.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||