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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(prandtl-d-root-ns) Prandtl-D root - NASA Preliminary Research Aerodynamic Design To Lower Drag | NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider root airfoil Max thickness 12% at 30.9% chord Max camber 3.5% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(ag46c03-il) AG46c -03f | Drela AG46c -03f airfoil Max thickness 6% at 23.3% chord Max camber 1.9% at 37.3% chord | Remove Airfoil details Airfoil plotter |
(goe571-il) GOE 571 AIRFOIL | Gottingen 571 airfoil Max thickness 24.9% at 29.4% chord Max camber 9.8% at 29.4% chord | Remove Airfoil details Airfoil plotter |
(dga1182-il) D.G.A. 1182 | D.G.A. 1182 airfoil Max thickness 7.6% at 30% chord Max camber 0.9% at 20% chord | Remove Airfoil details Airfoil plotter |
(goe584-il) GOE 584 AIRFOIL | Gottingen 584 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx79l100-il) FX 79-L-100 | Wortmann FX 79-L-100 symmetrical airfoil Max thickness 10.1% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(sc20012-il) NASA SC(2)-0012 AIRFOIL | NASA SC(2)-0012 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(mh110-il) MH 110 10.01% | Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord | Remove Airfoil details Airfoil plotter |
(kc135b-il) KC-135 BL124.32 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 13% at 40% chord Max camber 1.4% at 20% chord | Remove Airfoil details Airfoil plotter |
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL | Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord | Remove Airfoil details Airfoil plotter |
(rc510-il) NASA RC(5)-10 AIRFOIL | NASA/Langley RC(5)-10 rotorcraft airfoil Max thickness 10% at 40.1% chord Max camber 2.2% at 25.3% chord | Remove Airfoil details Airfoil plotter |
(k3311-il) K3311 (original) | Leon Kincaid K3311 airfoil (original) Max thickness 11% at 30% chord Max camber 3.3% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (prandtl-d-root-ns,ag46c03-il,goe571-il,dga1182-il,goe584-il,fx79l100-il,sc20012-il,mh110-il,kc135b-il,v13009-il,rc510-il,k3311-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| prandtl-d-root-ns | 50,000 | 9 | 22.8 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 100,000 | 9 | 51.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 200,000 | 9 | 76.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 500,000 | 9 | 102.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 1,000,000 | 9 | 117.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 2,000,000 | 9 | 119.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-root-ns | 5,000,000 | 9 | 128.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 50,000 | 9 | 30.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 50,000 | 5 | 33.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 100,000 | 9 | 44.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 100,000 | 5 | 44.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 200,000 | 9 | 58.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 200,000 | 5 | 55.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 500,000 | 9 | 74.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 500,000 | 5 | 72.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46c03-il | 1,000,000 | 9 | 88.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46c03-il | 1,000,000 | 5 | 86 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 50,000 | 9 | 3.7 at α=-12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 50,000 | 5 | 5.7 at α=-7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 100,000 | 9 | 8.1 at α=-8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 100,000 | 5 | 8.6 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 200,000 | 9 | 33.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 200,000 | 5 | 34 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 500,000 | 9 | 56.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 500,000 | 5 | 42.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe571-il | 1,000,000 | 9 | 62.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe571-il | 1,000,000 | 5 | 52.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 50,000 | 9 | 22.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 50,000 | 5 | 20.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 100,000 | 9 | 24.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 100,000 | 5 | 27.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 200,000 | 9 | 29.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 200,000 | 5 | 37.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 500,000 | 9 | 41.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 500,000 | 5 | 47.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 1,000,000 | 9 | 57.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 1,000,000 | 5 | 55.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 50,000 | 9 | 8.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 9 | 51.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 5 | 55 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 5 | 77.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 9 | 112.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 5 | 106 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 9 | 137.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 5 | 126.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 50,000 | 9 | 27.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 50,000 | 5 | 27 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 100,000 | 9 | 38.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 100,000 | 5 | 35.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 200,000 | 9 | 50.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 200,000 | 5 | 41.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 500,000 | 9 | 58 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 500,000 | 5 | 58.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx79l100-il | 1,000,000 | 9 | 70.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx79l100-il | 1,000,000 | 5 | 72.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 50,000 | 9 | 24.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 50,000 | 5 | 23.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 100,000 | 5 | 29.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 200,000 | 9 | 36 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 200,000 | 5 | 39.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 500,000 | 9 | 53.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 500,000 | 5 | 58.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 1,000,000 | 9 | 71.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 1,000,000 | 5 | 72.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 50,000 | 9 | 16.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 50,000 | 5 | 25.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 100,000 | 9 | 39 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 100,000 | 5 | 41 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 200,000 | 9 | 56.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 200,000 | 5 | 56 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 500,000 | 9 | 78.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 500,000 | 5 | 75.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh110-il | 1,000,000 | 9 | 94.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh110-il | 1,000,000 | 5 | 88.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 50,000 | 9 | 31.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 50,000 | 5 | 31.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 100,000 | 9 | 50.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 100,000 | 5 | 49.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 200,000 | 9 | 70.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 200,000 | 5 | 62.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 500,000 | 9 | 89.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 500,000 | 5 | 71.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 1,000,000 | 9 | 98.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 1,000,000 | 5 | 79.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 50,000 | 9 | 26.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 50,000 | 5 | 28.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 9 | 36.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 5 | 39.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 9 | 49.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 5 | 53.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 9 | 72.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 5 | 71.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 9 | 88.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 5 | 86.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 9 | 31.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 5 | 32.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 9 | 46.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 5 | 43.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 9 | 60.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 5 | 54.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 9 | 76.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 5 | 75.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 9 | 94.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 5 | 92.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 50,000 | 9 | 34.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 50,000 | 5 | 36.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 100,000 | 9 | 55.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 100,000 | 5 | 56.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 200,000 | 9 | 77.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 200,000 | 5 | 76.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 500,000 | 9 | 107.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 500,000 | 5 | 100.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 1,000,000 | 9 | 129.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 1,000,000 | 5 | 116.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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