NACA 23024 (naca23024-il)
NACA 23024 - NACA 23024 airfoil
| Details | Dat file | Parser | |
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(naca23024-il) NACA 23024 NACA 23024 airfoil Max thickness 24% at 30.3% chord. Max camber 2.9% at 1.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 23024 1.00000 0 0.95036 0.01724 0.90064 0.03115 0.80116 0.05687 0.70162 0.07988 0.60202 0.10008 0.50235 0.11690 0.40256 0.12928 0.30265 0.13546 0.25262 0.13535 0.20253 0.13237 0.15001 0.12528 0.09423 0.11049 0.06601 0.09844 0.03853 0.08172 0.01331 0.05764 0.00277 0.04017 0.00000 0.00000 0.02223 -0.03303 0.03669 -0.04432 0.06147 -0.05862 0.08399 -0.06860 0.10577 -0.07647 0.14999 -0.08852 0.19747 -0.09703 0.24738 -0.10223 0.29735 -0.10454 0.39744 -0.10278 0.49766 -0.09482 0.59798 -0.08242 0.69838 -0.06664 0.79884 -0.04803 0.89936 -0.02673 0.94964 -0.01504 1.00000 0.00000 |
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Polars for NACA 23024 (naca23024-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca23024-il | 50,000 | 9 | 16.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 50,000 | 5 | 19.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 100,000 | 9 | 34.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 100,000 | 5 | 28.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 200,000 | 9 | 41.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 200,000 | 5 | 33.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 500,000 | 9 | 44.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 500,000 | 5 | 43.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 1,000,000 | 9 | 56.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 1,000,000 | 5 | 54.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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