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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(oa213-il) ONERA OA213 AIRFOIL | ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12.6% at 32.5% chord Max camber 3.3% at 25% chord | Remove Airfoil details Airfoil plotter |
(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 |
(s4053-il) S4053 | Selig S4053 low Reynolds number airfoil Max thickness 8.9% at 30.9% chord Max camber 3% at 45% chord | Remove Airfoil details Airfoil plotter |
(s3002-il) SELIG 3002-099-83 | Selig S3002 low Reynolds number airfoil Max thickness 9.9% at 30.6% chord Max camber 2.3% at 49.8% chord | Remove Airfoil details Airfoil plotter |
(nplx-il) NPL AIRFOIL FROM ARC CP 1372 | NPL transonic airfoil FROM ARC CP 1372 Max thickness 10.7% at 35.8% chord Max camber 1.1% at 73.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oa213-il,oaf128-il,s4053-il,s3002-il,nplx-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oa213-il | 50,000 | 9 | 26.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 50,000 | 5 | 29.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 9 | 54 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 9 | 75.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 5 | 75.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 9 | 95.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 5 | 93.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| s4053-il | 50,000 | 9 | 38.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 50,000 | 5 | 39.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 100,000 | 9 | 58.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 100,000 | 5 | 57.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 200,000 | 9 | 80.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 200,000 | 5 | 75.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 500,000 | 9 | 109.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 500,000 | 5 | 96.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4053-il | 1,000,000 | 9 | 129 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4053-il | 1,000,000 | 5 | 109.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 50,000 | 9 | 35.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 50,000 | 5 | 39.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 100,000 | 9 | 56.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 100,000 | 5 | 55.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 200,000 | 9 | 76.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 200,000 | 5 | 70.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 500,000 | 9 | 99.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 500,000 | 5 | 89.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3002-il | 1,000,000 | 9 | 112.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3002-il | 1,000,000 | 5 | 100.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 50,000 | 9 | 22 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 50,000 | 5 | 22.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 100,000 | 9 | 28.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 100,000 | 5 | 28.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 200,000 | 9 | 41 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 200,000 | 5 | 38.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 500,000 | 9 | 49.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 500,000 | 5 | 54.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nplx-il | 1,000,000 | 9 | 62.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nplx-il | 1,000,000 | 5 | 70.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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