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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(raf26-il) RAF 26 AIRFOIL | RAF-26 airfoil Max thickness 6.6% at 29.9% chord Max camber 2.1% at 49.9% chord | Remove Airfoil details Airfoil plotter |
(sc20404-il) NASA SC(2)-0404 AIRFOIL | NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord | Remove Airfoil details Airfoil plotter |
(s9032-il) S9032 (9%) | Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 25% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(s813-nr) NREL's S813 Airfoil | NREL HAWT airfoil S813 tip Max thickness 16% at 40.4% chord Max camber 2.3% at 54.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (raf26-il,sc20404-il,s9032-il,s813-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf26-il | 50,000 | 9 | 34 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 50,000 | 5 | 37.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 100,000 | 9 | 53.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 100,000 | 5 | 51.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 200,000 | 9 | 71.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 200,000 | 5 | 62.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 500,000 | 9 | 88.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 500,000 | 5 | 69.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf26-il | 1,000,000 | 9 | 94.1 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf26-il | 1,000,000 | 5 | 76.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 50,000 | 9 | 20.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 50,000 | 5 | 19.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 100,000 | 9 | 37.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 100,000 | 5 | 26 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 200,000 | 9 | 35.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 200,000 | 5 | 35.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 500,000 | 9 | 52 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 500,000 | 5 | 41.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 1,000,000 | 9 | 49.7 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 1,000,000 | 5 | 55.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 50,000 | 9 | 23.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 50,000 | 5 | 25 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 100,000 | 9 | 32.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 100,000 | 5 | 34.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 200,000 | 9 | 43.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 200,000 | 5 | 44.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 500,000 | 9 | 60.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 500,000 | 5 | 61 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s9032-il | 1,000,000 | 9 | 74.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s9032-il | 1,000,000 | 5 | 74.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 50,000 | 9 | 23.5 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 50,000 | 5 | 20.4 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 100,000 | 9 | 35.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 100,000 | 5 | 34.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 200,000 | 9 | 64.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 200,000 | 5 | 65.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 500,000 | 9 | 104.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 500,000 | 5 | 96.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s813-nr | 1,000,000 | 9 | 130.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s813-nr | 1,000,000 | 5 | 115.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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