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 | ||
(goe324-il) GOE 324 (HANSA-BRANDENBURG) AIRFOIL | Gottingen 324 (Hansa-Brandenburg) airfoil Max thickness 13.1% at 29.8% chord Max camber 5.9% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe504-il) GOE 504 AIRFOIL | Gottingen 504 airfoil Max thickness 18% at 29.2% chord Max camber 5.4% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(fx74cl5140-il) FX74_CL5_140 | Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(mh117-il) MH 117 9.8% | Martin Hepperle MH 117 for a propeller for ultralight (tip) Max thickness 9.8% at 29.1% chord Max camber 2.7% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(fx66h80-il) FX 66-H-80 | Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord | Remove Airfoil details Airfoil plotter |
(fx66182-il) FX 66-182 AIRFOIL | Wortmann FX 66-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(fx66196v-il) FX 66-S-196 V1 AIRFOIL | Wortmann FX 66-S-196 V1 airfoil Max thickness 19.6% at 37.1% chord Max camber 4% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(fx77w258-il) WORTMANN FX 77-W-258 AIRFOIL | Wortmann FX 77-W-258 wind turbine airfoil Max thickness 26.1% at 30.9% chord Max camber 4.3% at 27.9% chord | Remove Airfoil details Airfoil plotter |
(rg15a111-il) RG 15A-1.8/11.0 AIRFOIL | Rolf Girsberger RG 15A-1.8/11.0 airfoil Max thickness 11% at 30.2% chord Max camber 1.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe765-il) Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300 | Used on the Me163 Komet Max thickness 14.4% at 30% chord Max camber 1.9% at 25.9% chord | Remove Airfoil details Airfoil plotter |
(e398-il) EPPLER 398 AIRFOIL | Eppler E398 human powered aircraft airfoil Max thickness 14.2% at 29.6% chord Max camber 5.3% at 50.9% chord | Remove Airfoil details Airfoil plotter |
(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED) | Airfoil measured from an ASW22 wing Max thickness 13.6% at 33.9% chord Max camber 3.1% at 45.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe324-il,goe504-il,fx74cl5140-il,mh117-il,fx66h80-il,fx66182-il,fx66196v-il,fx77w258-il,rg15a111-il,goe765-il,e398-il,du84132v-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe324-il | 50,000 | 9 | 8.3 at α=-3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 50,000 | 5 | 20 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 100,000 | 9 | 33.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 100,000 | 5 | 49.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 200,000 | 9 | 70.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 200,000 | 5 | 74.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 500,000 | 9 | 108.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 500,000 | 5 | 104.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe324-il | 1,000,000 | 9 | 136.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe324-il | 1,000,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 50,000 | 9 | 3.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 50,000 | 5 | 13.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 100,000 | 9 | 34.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 100,000 | 5 | 43.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 200,000 | 9 | 66.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 200,000 | 5 | 62.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 500,000 | 9 | 91.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 500,000 | 5 | 85.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe504-il | 1,000,000 | 9 | 114.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe504-il | 1,000,000 | 5 | 104.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 9 | 6.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 5 | 18.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 9 | 33.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 5 | 46.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 9 | 72.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 5 | 73.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 9 | 118.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 5 | 115.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 9 | 156.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 5 | 149.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 50,000 | 5 | 38.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 100,000 | 9 | 56.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 100,000 | 5 | 55.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 200,000 | 9 | 77 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 200,000 | 5 | 72 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 500,000 | 9 | 102.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 500,000 | 5 | 90.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh117-il | 1,000,000 | 9 | 120.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh117-il | 1,000,000 | 5 | 100.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 50,000 | 9 | 32.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 50,000 | 5 | 31.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 9 | 47.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 100,000 | 5 | 47.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 9 | 63 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 200,000 | 5 | 62.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 9 | 87.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 500,000 | 5 | 83.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 9 | 105.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66h80-il | 1,000,000 | 5 | 98.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 50,000 | 9 | 4.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 50,000 | 5 | 8.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 100,000 | 9 | 5.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 100,000 | 5 | 30.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 200,000 | 9 | 61.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 200,000 | 5 | 67.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 500,000 | 9 | 107.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 500,000 | 5 | 104.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66182-il | 1,000,000 | 9 | 134.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66182-il | 1,000,000 | 5 | 128.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 50,000 | 9 | 4.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 50,000 | 5 | 7.8 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 100,000 | 9 | 5.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 100,000 | 5 | 26.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 200,000 | 9 | 49.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 200,000 | 5 | 61.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 500,000 | 9 | 110.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 500,000 | 5 | 104.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66196v-il | 1,000,000 | 9 | 139 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66196v-il | 1,000,000 | 5 | 132.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 50,000 | 9 | 1.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 50,000 | 5 | 2.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 100,000 | 9 | 1.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 100,000 | 5 | 10.5 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 200,000 | 9 | 9.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 200,000 | 5 | 36.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 500,000 | 9 | 76 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 500,000 | 5 | 83.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx77w258-il | 1,000,000 | 9 | 112.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx77w258-il | 1,000,000 | 5 | 103.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 9 | 32.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 50,000 | 5 | 35.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 9 | 50 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 9 | 66.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 200,000 | 5 | 62.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 9 | 87.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 500,000 | 5 | 79.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 9 | 101.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15a111-il | 1,000,000 | 5 | 90 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 50,000 | 9 | 15.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 50,000 | 5 | 28.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 9 | 41.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 100,000 | 5 | 44.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 9 | 59.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 200,000 | 5 | 58.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 9 | 80.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 500,000 | 5 | 68.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 9 | 85.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe765-il | 1,000,000 | 5 | 79.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 50,000 | 9 | 6.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 50,000 | 5 | 17.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 100,000 | 9 | 47.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 100,000 | 5 | 54.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 200,000 | 9 | 84.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 200,000 | 5 | 86.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 500,000 | 9 | 129 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 500,000 | 5 | 124.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 9 | 163.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 5 | 147 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 50,000 | 9 | 31.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 50,000 | 5 | 34.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 100,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 100,000 | 5 | 52.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 200,000 | 9 | 71.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 200,000 | 5 | 62.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 500,000 | 9 | 82 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 500,000 | 5 | 75.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du84132v-il | 1,000,000 | 9 | 92.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du84132v-il | 1,000,000 | 5 | 82.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||