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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(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 |
(s809-nr) NREL's S809 Airfoil | NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord | Remove Airfoil details Airfoil plotter |
(s3-il) REPUBLIC S-3 AIRFOIL | Republic S-3 airfoil (P-47 wing airfoil) Max thickness 11% at 30% chord Max camber 1.8% at 15% chord | Remove Airfoil details Airfoil plotter |
(ssca07-il) SIKORSKY SSC-A07 AIRFOIL | Sikorsky/Flemming SSC-A07 transonic rotorcraft airfoil Max thickness 7% at 37.7% chord Max camber 0.9% at 17.2% chord | Remove Airfoil details Airfoil plotter |
(c5d-il) LOCKHEED C-5A BL758.6 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 60% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s9032-il,s809-nr,s3-il,ssca07-il,c5d-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| s809-nr | 50,000 | 9 | 15.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 50,000 | 5 | 13.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 9 | 23.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 5 | 26.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 5 | 53.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 9 | 81.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 5 | 75.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 9 | 100.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 5 | 89.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 50,000 | 9 | 23.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 50,000 | 5 | 28.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 100,000 | 9 | 38.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 100,000 | 5 | 42.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 200,000 | 9 | 56.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 200,000 | 5 | 56.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 500,000 | 9 | 76.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 500,000 | 5 | 73.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 1,000,000 | 9 | 91.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 1,000,000 | 5 | 85.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 50,000 | 9 | 29.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 50,000 | 5 | 28.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 100,000 | 9 | 39.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 100,000 | 5 | 37.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 200,000 | 9 | 50.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 200,000 | 5 | 48.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 500,000 | 9 | 64.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 500,000 | 5 | 61.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ssca07-il | 1,000,000 | 9 | 76 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ssca07-il | 1,000,000 | 5 | 74.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 50,000 | 9 | 30.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 50,000 | 5 | 31 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 100,000 | 9 | 48.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 100,000 | 5 | 44.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 200,000 | 9 | 66.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 200,000 | 5 | 53.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 500,000 | 9 | 75.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 500,000 | 5 | 62.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5d-il | 1,000,000 | 9 | 79.9 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5d-il | 1,000,000 | 5 | 78.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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