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 |
(ah82150f-il) AH 82-150 F | Althaus AH 82-150 F airfoil Max thickness 15% at 43.5% chord Max camber 3.6% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(fx71089a-il) WORTMANN FX 71-089A AIRFOIL | Wortmann FX 71-089A airfoil Max thickness 8.9% at 22.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e1230-il) EPPLER 1230 AIRFOIL | Eppler E1230 general aviation airfoil (Long-EZ and Defiant wing airfoil) Max thickness 17.4% at 30.9% chord Max camber 3.6% at 25.6% chord | Remove Airfoil details Airfoil plotter |
(hq1512-il) HQ 1.5/12 AIRFOIL | Quabeck HQ 1.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(s1221-flap-il) S1221 w/ 4 deg flap | Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord | Remove Airfoil details Airfoil plotter |
(e341-il) EPPLER 341 AIRFOIL | Eppler E341 flying wing airfoil Max thickness 13.9% at 32.8% chord Max camber 3% at 23.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (defcnd2-il,r1082t-il,usa35b-il,naca651212a06-il,rae69ck-il,ah82150f-il,fx71089a-il,e1230-il,hq1512-il,s1221-flap-il,e341-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 | |
| ah82150f-il | 50,000 | 9 | 17.6 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150f-il | 50,000 | 5 | 19.4 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150f-il | 100,000 | 9 | 34.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150f-il | 100,000 | 5 | 33.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150f-il | 200,000 | 9 | 58.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150f-il | 200,000 | 5 | 53.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150f-il | 500,000 | 9 | 95.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150f-il | 500,000 | 5 | 99.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150f-il | 1,000,000 | 9 | 135.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150f-il | 1,000,000 | 5 | 133.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 50,000 | 9 | 19.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 50,000 | 5 | 19.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 9 | 25.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 100,000 | 5 | 26.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 9 | 31.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 200,000 | 5 | 36.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 9 | 46.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 500,000 | 5 | 52.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 9 | 59.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71089a-il | 1,000,000 | 5 | 68 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 50,000 | 9 | 16.7 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 50,000 | 5 | 24.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 9 | 35.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 9 | 56.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 5 | 60.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 9 | 85.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 5 | 86.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 9 | 111.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 5 | 104.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1512-il | 50,000 | 9 | 32.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1512-il | 50,000 | 5 | 33.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1512-il | 100,000 | 9 | 49.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1512-il | 100,000 | 5 | 48.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1512-il | 200,000 | 9 | 67.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1512-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1512-il | 500,000 | 9 | 82.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1512-il | 500,000 | 5 | 73.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1512-il | 1,000,000 | 9 | 93.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1512-il | 1,000,000 | 5 | 81.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 9 | 31 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 5 | 39.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 9 | 48.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 5 | 56.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 9 | 69.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 5 | 76.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 9 | 104.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 5 | 106.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 9 | 133.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 5 | 129.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 50,000 | 9 | 13.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 50,000 | 5 | 23.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 100,000 | 9 | 28.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 100,000 | 5 | 42.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 200,000 | 9 | 59.1 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 200,000 | 5 | 60.1 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 500,000 | 9 | 85.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 500,000 | 5 | 80.7 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e341-il | 1,000,000 | 9 | 102.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e341-il | 1,000,000 | 5 | 101.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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