NACA 0021 (naca0021-il)
NACA 0021 - NACA 0021 airfoil
| Details | Dat file | Parser | |
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(naca0021-il) NACA 0021 NACA 0021 airfoil Max thickness 21% at 30% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 0021 1.0000 0.00221 0.9500 0.01412 0.9000 0.02534 0.8000 0.04591 0.7000 0.06412 0.6000 0.07986 0.5000 0.09265 0.4000 0.10156 0.3000 0.10504 0.2500 0.10397 0.2000 0.10040 0.1500 0.09354 0.1000 0.08195 0.0750 0.07350 0.0500 0.06221 0.0250 0.04576 0.0125 0.03315 0.0000 0.00000 0.0125 -0.03315 0.0250 -0.04576 0.0500 -0.06221 0.0750 -0.07350 0.1000 -0.08195 0.1500 -0.09354 0.2000 -0.10040 0.2500 -0.10397 0.3000 -0.10504 0.4000 -0.10156 0.5000 -0.09265 0.6000 -0.07986 0.7000 -0.06412 0.8000 -0.04591 0.9000 -0.02534 0.9500 -0.01412 1.0000 -0.00221 |
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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 0021 (naca0021-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca0021-il | 50,000 | 9 | 19.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 50,000 | 5 | 25.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 100,000 | 9 | 36.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 100,000 | 5 | 35.6 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 200,000 | 9 | 48 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 200,000 | 5 | 43.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 500,000 | 9 | 60.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 500,000 | 5 | 56.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca0021-il | 1,000,000 | 9 | 74.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca0021-il | 1,000,000 | 5 | 71 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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