NACA 23015 (naca23015-il)
NACA 23015 - NACA 23015 airfoil
| Details | Dat file | Parser | |
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(naca23015-il) NACA 23015 NACA 23015 airfoil Max thickness 15% at 30% chord. Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 23015 1.0000 0.0016 0.9500 0.0112 0.9000 0.0204 0.8000 0.0373 0.7000 0.0525 0.6000 0.0661 0.5000 0.0774 0.4000 0.0859 0.3000 0.0905 0.2500 0.0908 0.2000 0.0892 0.1500 0.0852 0.1000 0.0764 0.0750 0.0690 0.0500 0.0589 0.0250 0.0444 0.0125 0.0334 0.0000 0.0000 0.0125 -0.0154 0.0250 -0.0225 0.0500 -0.0304 0.0750 -0.0361 0.1000 -0.0409 0.1500 -0.0484 0.2000 -0.0541 0.2500 -0.0578 0.3000 -0.0596 0.4000 -0.0592 0.5000 -0.0550 0.6000 -0.0481 0.7000 -0.0391 0.8000 -0.0283 0.9000 -0.0159 0.9500 -0.0090 1.0000 -0.0016 |
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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 23015 (naca23015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca23015-il | 50,000 | 9 | 21 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 50,000 | 5 | 27.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 100,000 | 9 | 33.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 100,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 200,000 | 9 | 48.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 200,000 | 5 | 52.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 500,000 | 9 | 72 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 500,000 | 5 | 74.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23015-il | 1,000,000 | 9 | 91 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23015-il | 1,000,000 | 5 | 91.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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