NACA 23021 (naca23021-il)
NACA 23021 - NACA 23021 airfoil
| Details | Dat file | Parser | |
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(naca23021-il) NACA 23021 NACA 23021 airfoil Max thickness 21% at 30% chord. Max camber 1.9% at 10% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 23021 1.0000 0.0022 0.9500 0.0153 0.9000 0.0276 0.8000 0.0505 0.7000 0.0709 0.6000 0.0890 0.5000 0.1040 0.4000 0.1149 0.3000 0.1206 0.2500 0.1205 0.2000 0.1180 0.1500 0.1119 0.1000 0.1003 0.0750 0.0913 0.0500 0.0793 0.0250 0.0641 0.0125 0.0487 0.0000 0.0000 0.0125 -0.0208 0.0250 -0.0314 0.0500 -0.0452 0.0750 -0.0555 0.1000 -0.0632 0.1500 -0.0751 0.2000 -0.0830 0.2500 -0.0876 0.3000 -0.0895 0.4000 -0.0883 0.5000 -0.0814 0.6000 -0.0707 0.7000 -0.0572 0.8000 -0.0413 0.9000 -0.0230 0.9500 -0.0130 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 23021 (naca23021-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca23021-il | 50,000 | 9 | 18.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 50,000 | 5 | 24.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 100,000 | 9 | 37 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 100,000 | 5 | 35.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 200,000 | 9 | 49.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 200,000 | 5 | 42.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 500,000 | 9 | 56.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 500,000 | 5 | 50.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23021-il | 1,000,000 | 9 | 64.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23021-il | 1,000,000 | 5 | 55.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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