NACA 2424 (naca2424-il)
NACA 2424 - NACA 2424 airfoil
| Details | Dat file | Parser | |
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(naca2424-il) NACA 2424 NACA 2424 airfoil Max thickness 24% at 29.7% chord. Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 2424 1.00000 0 0.95098 0.01930 0.90161 0.03502 0.80233 0.06352 0.70244 0.08824 0.60203 0.10903 0.50118 0.12532 0.40000 0.13606 0.29700 0.13874 0.24555 0.13593 0.19427 0.12959 0.14333 0.11888 0.09300 0.10215 0.06820 0.09052 0.04380 0.07552 0.02012 0.05449 0.00855 0.03892 0.00000 0.00000 0.01615 -0.03646 0.02988 -0.04965 0.05620 -0.06614 0.08180 -0.07692 0.10700 -0.08465 0.15667 -0.09450 0.20573 -0.09959 0.25445 -0.10155 0.30300 -0.10124 0.40000 -0.09606 0.49882 -0.08644 0.59797 -0.07347 0.69756 -0.05824 0.79767 -0.04130 0.89839 -0.02280 0.94902 -0.01292 1.00000 0.00000 |
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Polars for NACA 2424 (naca2424-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2424-il | 50,000 | 9 | 1.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 50,000 | 5 | 15.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 100,000 | 9 | 36.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 100,000 | 5 | 33.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 200,000 | 9 | 49 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 200,000 | 5 | 40.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 500,000 | 9 | 55 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 500,000 | 5 | 49.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2424-il | 1,000,000 | 9 | 65.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2424-il | 1,000,000 | 5 | 58.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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