NACA 2408 (naca2408-il)
NACA 2408 - NACA 2408 airfoil
| Details | Dat file | Parser | |
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(naca2408-il) NACA 2408 NACA 2408 airfoil Max thickness 8% at 29.9% chord. Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA 2408 1.00000 0.00084 0.95033 0.00855 0.90054 0.01575 0.80078 0.02858 0.70081 0.03942 0.60068 0.04820 0.50039 0.05473 0.40000 0.05869 0.29900 0.05875 0.24852 0.05677 0.19809 0.05320 0.14778 0.04776 0.09768 0.03987 0.07273 0.03471 0.04794 0.02829 0.02337 0.01944 0.01128 0.01380 0.00000 0.00000 0.01372 -0.01134 0.02663 -0.01493 0.05206 -0.01891 0.07727 -0.02111 0.10232 -0.02237 0.15222 -0.02338 0.20191 -0.02320 0.25148 -0.02239 0.30100 -0.02125 0.40000 -0.01869 0.49961 -0.01585 0.59932 -0.01264 0.69919 -0.00942 0.79922 -0.00636 0.89946 -0.00353 0.94967 -0.00217 1.00000 -0.00084 |
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Polars for NACA 2408 (naca2408-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca2408-il | 50,000 | 9 | 37.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 50,000 | 5 | 36.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 9 | 52.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 100,000 | 5 | 48.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 9 | 66.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 200,000 | 5 | 58.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 9 | 80.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 500,000 | 5 | 67.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 9 | 86.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca2408-il | 1,000,000 | 5 | 82.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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