NACA 4421 (naca4421-il)
NACA 4421 - NACA 4421 airfoil
| Details | Dat file | Parser | |
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(naca4421-il) NACA 4421 NACA 4421 airfoil Max thickness 21% at 30% chord. Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 4421 1.0000 0.0022 0.9500 0.0211 0.9000 0.0385 0.8000 0.0691 0.7000 0.0950 0.6000 0.1160 0.5000 0.1318 0.4000 0.1416 0.3000 0.1427 0.2500 0.1388 0.2000 0.1317 0.1500 0.1204 0.1000 0.1035 0.0750 0.0924 0.0500 0.0782 0.0250 0.0584 0.0125 0.0445 0.0000 0.0000 0.0125 -0.0242 0.0250 -0.0348 0.0500 -0.0478 0.0750 -0.0562 0.1000 -0.0615 0.1500 -0.0675 0.2000 -0.0698 0.2500 -0.0692 0.3000 -0.0676 0.4000 -0.0616 0.5000 -0.0534 0.6000 -0.0440 0.7000 -0.0335 0.8000 -0.0231 0.9000 -0.0127 0.9500 -0.0074 1.0000 -0.0022 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NACA 4421 (naca4421-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca4421-il | 50,000 | 9 | 3.6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4421-il | 50,000 | 5 | 15.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4421-il | 100,000 | 9 | 36.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4421-il | 100,000 | 5 | 41.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4421-il | 200,000 | 9 | 61.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4421-il | 200,000 | 5 | 58.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4421-il | 500,000 | 9 | 83.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4421-il | 500,000 | 5 | 78.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4421-il | 1,000,000 | 9 | 103.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4421-il | 1,000,000 | 5 | 93.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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