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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(oaf128-il) OAF128 AIRFOIL | ONERA/Aerospatiale OAF128 Fenestron airfoil Max thickness 12.8% at 23.2% chord Max camber 1% at 43.7% chord | Remove Airfoil details Airfoil plotter |
(goe278-il) GOE 278 (DAIMLER IX) AIRFOIL | Gottingen 278 (DAIMLER IX) airfoil Max thickness 7.4% at 29.9% chord Max camber 4.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(cr1-il) CURTISS CR-1 AIRFOIL | Curtiss CR-1 general aviation airfoil Max thickness 12.2% at 24% chord Max camber 4.7% at 42% chord | Remove Airfoil details Airfoil plotter |
(goe776-il) GOE 776 AIRFOIL | Gottingen 776 airfoil Max thickness 25% at 30% chord Max camber 0% at 60% chord | Remove Airfoil details Airfoil plotter |
(goe234-il) GOE 234 (MVA CA5) AIRFOIL | Gottingen 234 (MVA CA5) airfoil Max thickness 14.2% at 19.7% chord Max camber 9.2% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(goe758-il) GOE 758 AIRFOIL | Gottingen 758 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(hs1620-il) HAM-STD HS1-620 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 20% at 34% chord Max camber 4.1% at 44% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oaf128-il,goe278-il,cr1-il,goe776-il,goe234-il,goe758-il,hs1620-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oaf128-il | 50,000 | 9 | 24.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 50,000 | 5 | 31.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 100,000 | 9 | 41.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 100,000 | 5 | 43.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 200,000 | 9 | 56.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 200,000 | 5 | 55.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 500,000 | 9 | 74.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 500,000 | 5 | 71 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 1,000,000 | 9 | 85.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 1,000,000 | 5 | 85.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 50,000 | 9 | 38.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 50,000 | 5 | 40.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 100,000 | 9 | 55.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 100,000 | 5 | 56.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 200,000 | 9 | 72.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 200,000 | 5 | 72.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 500,000 | 9 | 95.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 500,000 | 5 | 92.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 1,000,000 | 9 | 113.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 1,000,000 | 5 | 102.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr1-il | 50,000 | 9 | 22.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr1-il | 50,000 | 5 | 32.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr1-il | 100,000 | 9 | 54.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr1-il | 100,000 | 5 | 53 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr1-il | 200,000 | 9 | 79.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr1-il | 200,000 | 5 | 72.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr1-il | 500,000 | 9 | 109.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr1-il | 500,000 | 5 | 89.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cr1-il | 1,000,000 | 9 | 120.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cr1-il | 1,000,000 | 5 | 104.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe776-il | 50,000 | 9 | 6.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe776-il | 50,000 | 5 | 19.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe776-il | 100,000 | 9 | 33.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe776-il | 100,000 | 5 | 28.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe776-il | 200,000 | 9 | 41.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe776-il | 200,000 | 5 | 35.1 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe776-il | 500,000 | 9 | 50 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe776-il | 500,000 | 5 | 48.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe776-il | 1,000,000 | 9 | 66.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe776-il | 1,000,000 | 5 | 61.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 50,000 | 9 | 10.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 50,000 | 5 | 27.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 100,000 | 9 | 54.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 100,000 | 5 | 56.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 200,000 | 9 | 77 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 200,000 | 5 | 79.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 500,000 | 9 | 110.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 500,000 | 5 | 108.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe234-il | 1,000,000 | 9 | 137.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe234-il | 1,000,000 | 5 | 127.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 50,000 | 9 | 7.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 50,000 | 5 | 25.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 100,000 | 9 | 45.4 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 100,000 | 5 | 52.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 200,000 | 9 | 73.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 200,000 | 5 | 75.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 500,000 | 9 | 108.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 500,000 | 5 | 102.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe758-il | 1,000,000 | 9 | 133.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe758-il | 1,000,000 | 5 | 123.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 50,000 | 9 | 16 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 50,000 | 5 | 25.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 100,000 | 9 | 43.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 100,000 | 5 | 38.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 200,000 | 9 | 59.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 200,000 | 5 | 51.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 500,000 | 9 | 72.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 500,000 | 5 | 57.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 1,000,000 | 9 | 76.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 1,000,000 | 5 | 70.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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