Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(defcnd2-il) DEFIANT CANARD BL110 AIRFOIL | Rutan DEFIANT canard BL110 airfoil Max thickness 14.7% at 28.6% chord Max camber 3.8% at 28.6% chord | Remove Airfoil details Airfoil plotter |
(r1082t-il) RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL | Roncz 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord Max camber 3% at 40% chord | Remove Airfoil details Airfoil plotter |
(usa35b-il) USA-35B AIRFOIL | USA-35B airfoil Max thickness 11.6% at 30% chord Max camber 4.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(naca651212a06-il) NACA 65(1)-212 a=0.6 | NACA 65(1)-212 a=0.6 airfoil Max thickness 12% at 40% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(rae69ck-il) RAE6-9CK AIRFOIL | RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (defcnd2-il,r1082t-il,usa35b-il,naca651212a06-il,rae69ck-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| defcnd2-il | 50,000 | 9 | 8.4 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 50,000 | 5 | 28.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 100,000 | 9 | 41.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 100,000 | 5 | 47.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 200,000 | 9 | 64.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 200,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 500,000 | 9 | 89.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 500,000 | 5 | 89.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 1,000,000 | 9 | 117.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 1,000,000 | 5 | 115 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 50,000 | 9 | 21.7 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 50,000 | 5 | 16.5 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 100,000 | 9 | 34.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 100,000 | 5 | 38.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 200,000 | 9 | 73.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 200,000 | 5 | 69.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 500,000 | 9 | 107.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 500,000 | 5 | 101.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 1,000,000 | 9 | 135 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 1,000,000 | 5 | 122.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 50,000 | 9 | 24.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 50,000 | 5 | 36.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 100,000 | 9 | 53.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 100,000 | 5 | 56.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 200,000 | 9 | 76.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 200,000 | 5 | 75.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 500,000 | 9 | 106 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 500,000 | 5 | 97 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35b-il | 1,000,000 | 9 | 125.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35b-il | 1,000,000 | 5 | 113.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 50,000 | 9 | 25.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 50,000 | 5 | 29.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 100,000 | 9 | 46.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 100,000 | 5 | 45.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 200,000 | 9 | 66.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 200,000 | 5 | 56.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 500,000 | 9 | 81.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 500,000 | 5 | 69.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca651212a06-il | 1,000,000 | 9 | 94.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca651212a06-il | 1,000,000 | 5 | 75.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 50,000 | 9 | 25.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 50,000 | 5 | 27 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 100,000 | 9 | 37.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 100,000 | 5 | 37.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 200,000 | 9 | 53.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 200,000 | 5 | 49.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 500,000 | 9 | 70.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 500,000 | 5 | 57.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae69ck-il | 1,000,000 | 9 | 79 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae69ck-il | 1,000,000 | 5 | 69.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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