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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(usa98-il) USA 98 AIRFOIL | USA-98 airfoil Max thickness 14.3% at 30% chord Max camber 6.4% at 50% chord | Remove Airfoil details Airfoil plotter |
(stcyr172-il) St. CYR 172 (Royer) | St. CYR 172 (Royer) airfoil Max thickness 13.6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca747a415-il) NACA 747A415 | NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord | Remove Airfoil details Airfoil plotter |
(naca000834-il) NACA 0008-34 | NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa98-il,stcyr172-il,naca747a415-il,naca000834-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa98-il | 50,000 | 9 | 8.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 50,000 | 5 | 26.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 9 | 54.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 100,000 | 5 | 59.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 9 | 84.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 200,000 | 5 | 84.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 9 | 120.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 500,000 | 5 | 112.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 9 | 147.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa98-il | 1,000,000 | 5 | 124.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 50,000 | 9 | 22.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 50,000 | 5 | 27 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 100,000 | 9 | 37.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 100,000 | 5 | 38.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 200,000 | 9 | 51.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 200,000 | 5 | 50.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 500,000 | 9 | 66.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 500,000 | 5 | 61.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| stcyr172-il | 1,000,000 | 9 | 74.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| stcyr172-il | 1,000,000 | 5 | 75.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 9 | 19 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 5 | 17 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 9 | 37.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 5 | 44.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 5 | 66.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 9 | 97.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 5 | 92.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 9 | 120.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 5 | 110.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 50,000 | 9 | 18.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 50,000 | 5 | 18.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 100,000 | 9 | 24.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 100,000 | 5 | 30.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 200,000 | 9 | 40.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 200,000 | 5 | 36 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 500,000 | 9 | 57.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 500,000 | 5 | 37.4 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca000834-il | 1,000,000 | 9 | 43 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca000834-il | 1,000,000 | 5 | 42.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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