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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(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL | Eppler STE 87(-3)-914 airfoil Max thickness 14.6% at 34.1% chord Max camber 4.2% at 58.3% chord | Remove Airfoil details Airfoil plotter |
(sa7024-il) SA7024 | Selig / Ashok Gopalarathnam SA7024 low Reynolds number airfoil Max thickness 7% at 25.9% chord Max camber 3.3% at 43.3% chord | Remove Airfoil details Airfoil plotter |
(s9027-il) S9027 (8%) | Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ste87391-il,sa7024-il,s9027-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ste87391-il | 50,000 | 9 | 32.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 50,000 | 5 | 30.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 100,000 | 9 | 51.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 100,000 | 5 | 45.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 200,000 | 9 | 69.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 200,000 | 5 | 61.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 500,000 | 9 | 97.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 500,000 | 5 | 92.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ste87391-il | 1,000,000 | 9 | 146 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ste87391-il | 1,000,000 | 5 | 106.6 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7024-il | 50,000 | 9 | 38.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7024-il | 50,000 | 5 | 42.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7024-il | 100,000 | 9 | 59.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7024-il | 100,000 | 5 | 59 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7024-il | 200,000 | 9 | 80.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7024-il | 200,000 | 5 | 74.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7024-il | 500,000 | 9 | 105.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7024-il | 500,000 | 5 | 93.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sa7024-il | 1,000,000 | 9 | 122.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sa7024-il | 1,000,000 | 5 | 107.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 50,000 | 9 | 22.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 50,000 | 5 | 23.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 9 | 30.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 100,000 | 5 | 32.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 9 | 40.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 200,000 | 5 | 43.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 9 | 57.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 500,000 | 5 | 59.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 9 | 71.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9027-il | 1,000,000 | 5 | 73.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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