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 | ||
(fx74080-il) WORTMANN FX 74-080 | Wortmann FX 74-080 airfoil Max thickness 8.2% at 43.5% chord Max camber 4.3% at 46.7% chord | Remove Airfoil details Airfoil plotter |
(raf32md-il) RAF 32 MOD AIRFOIL | RAF-32 MOD airfoil Max thickness 10.2% at 30% chord Max camber 4% at 50% 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 |
(raf89-il) RAF 89 AIRFOIL | RAF-89 airfoil Max thickness 25% at 30% chord Max camber 1.6% at 50% chord | Remove Airfoil details Airfoil plotter |
(npl9660-il) NPL 9660 AIRFOIL | NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
(goe382-il) GOE 382 AIRFOIL | Gottingen 382 airfoil Max thickness 20% at 29% chord Max camber 6% at 39% chord | Remove Airfoil details Airfoil plotter |
(goe647-il) GOE 647 AIRFOIL | Gottingen 647 airfoil Max thickness 16.2% at 19.5% chord Max camber 5.3% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(goe117-il) GOE 117 (MVA MK.4) AIRFOIL | Gottingen 117 (MVA MK.4) airfoil Max thickness 9% at 29.8% chord Max camber 4.6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(nacam6-il) NACA M6 | NACA M6 airfoil Max thickness 12% at 30% chord Max camber 2.1% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (fx74080-il,raf32md-il,du84132v-il,raf89-il,npl9660-il,goe382-il,goe647-il,goe117-il,nacam6-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74080-il | 50,000 | 9 | 24.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 50,000 | 5 | 27.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 9 | 39.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 100,000 | 5 | 58 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 9 | 80.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 200,000 | 5 | 87 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 9 | 134.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 500,000 | 5 | 131.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 9 | 173.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74080-il | 1,000,000 | 5 | 164.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 50,000 | 9 | 38 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 50,000 | 5 | 37.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 9 | 62.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 100,000 | 5 | 61.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 9 | 87.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 200,000 | 5 | 83.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 9 | 120.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 500,000 | 5 | 110.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf32md-il | 1,000,000 | 5 | 124.3 at α=3.5° | 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 | |
| raf89-il | 50,000 | 9 | 1.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 50,000 | 5 | 7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 9 | 18.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 5 | 27.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 9 | 45.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 5 | 36 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 9 | 50.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 5 | 39.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 9 | 56.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 5 | 45.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 50,000 | 9 | 28 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 50,000 | 5 | 30.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 9 | 41.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 5 | 41.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 9 | 54.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 5 | 51.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 9 | 69.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 5 | 66.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 9 | 81.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 5 | 75.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 50,000 | 9 | 3.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 50,000 | 5 | 14 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 100,000 | 9 | 25.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 100,000 | 5 | 39.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 200,000 | 9 | 60.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 200,000 | 5 | 59.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 500,000 | 9 | 87 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 500,000 | 5 | 81.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 1,000,000 | 9 | 109.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 1,000,000 | 5 | 103.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 50,000 | 9 | 13.1 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 100,000 | 5 | 44.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 200,000 | 9 | 59 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 200,000 | 5 | 58.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 500,000 | 9 | 81.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 500,000 | 5 | 81.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 1,000,000 | 9 | 105.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 1,000,000 | 5 | 104.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe117-il | 50,000 | 9 | 32.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe117-il | 50,000 | 5 | 38.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe117-il | 100,000 | 9 | 58.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe117-il | 100,000 | 5 | 58.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe117-il | 200,000 | 9 | 78.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe117-il | 200,000 | 5 | 77.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe117-il | 500,000 | 9 | 107.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe117-il | 500,000 | 5 | 104.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe117-il | 1,000,000 | 9 | 131.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe117-il | 1,000,000 | 5 | 116.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 50,000 | 9 | 30.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 50,000 | 5 | 32.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 100,000 | 9 | 49.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 100,000 | 5 | 49.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 200,000 | 9 | 67.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 200,000 | 5 | 64.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 500,000 | 9 | 89.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 500,000 | 5 | 72.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam6-il | 1,000,000 | 9 | 90.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam6-il | 1,000,000 | 5 | 81 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||