NACA 1408 (naca1408-il)
NACA 1408 - NACA 1408 airfoil
| Details | Dat file | Parser | |
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(naca1408-il) NACA 1408 NACA 1408 airfoil Max thickness 8% at 30% chord. Max camber 1% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 1408 1.00000 0.00084 0.95016 0.00698 0.90027 0.01271 0.80039 0.02305 0.70041 0.03193 0.60034 0.03931 0.50020 0.04502 0.40000 0.04869 0.29950 0.04939 0.24926 0.04819 0.19904 0.04574 0.14889 0.04171 0.09883 0.03558 0.07386 0.03138 0.04896 0.02602 0.02418 0.01862 0.01189 0.01324 0.00000 0.00000 0.01311 -0.01200 0.02582 -0.01620 0.05104 -0.02134 0.07614 -0.02458 0.10117 -0.02682 0.15111 -0.02953 0.20096 -0.03074 0.25074 -0.03101 0.30050 -0.03063 0.40000 -0.02869 0.49980 -0.02556 0.59966 -0.02153 0.69959 -0.01693 0.79961 -0.01193 0.89973 -0.00659 0.94984 -0.00378 1.00000 -0.00084 |
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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 1408 (naca1408-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca1408-il | 50,000 | 9 | 32.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 50,000 | 5 | 31.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 100,000 | 9 | 44.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 100,000 | 5 | 40.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 200,000 | 9 | 54.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 200,000 | 5 | 47.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 500,000 | 9 | 66.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 500,000 | 5 | 62.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca1408-il | 1,000,000 | 9 | 72.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca1408-il | 1,000,000 | 5 | 77.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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