NACA 4424 (naca4424-il)
NACA 4424 - NACA 4424 airfoil
| Details | Dat file | Parser | |
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(naca4424-il) NACA 4424 NACA 4424 airfoil Max thickness 24% at 29.4% chord. Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 4424 1.00000 0 0.95196 0.02240 0.90320 0.04099 0.80464 0.07447 0.70487 0.10312 0.60405 0.12674 0.50235 0.14474 0.40000 0.15606 0.29401 0.15738 0.24111 0.15287 0.18858 0.14416 0.13674 0.13045 0.08611 0.11012 0.06153 0.09651 0.03775 0.07942 0.01536 0.05624 0.00530 0.03964 0.00000 0.00000 0.01970 -0.03472 0.03464 -0.04656 0.06225 -0.06066 0.08847 -0.06931 0.11389 -0.07512 0.16326 -0.08169 0.21142 -0.08416 0.25889 -0.08411 0.30599 -0.08238 0.40000 -0.07606 0.49765 -0.06698 0.59595 -0.05562 0.69513 -0.04312 0.79536 -0.03003 0.89680 -0.01655 0.94804 -0.00964 1.00000 0.00000 |
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Polars for NACA 4424 (naca4424-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca4424-il | 50,000 | 9 | 2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 50,000 | 5 | 8.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 100,000 | 9 | 30.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 100,000 | 5 | 33.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 200,000 | 9 | 53.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 200,000 | 5 | 45.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 500,000 | 9 | 64.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 500,000 | 5 | 55.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca4424-il | 1,000,000 | 9 | 73.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca4424-il | 1,000,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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