M6 (85%) (m685-il)
M6 (85%) - NACA/Munk M6 (85%)
| Details | Dat file | Parser | |
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(m685-il) M6 (85%) NACA/Munk M6 (85%) Max thickness 10.2% at 30% chord. Max camber 1.9% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
M6 (85%) 1 0 0.95 0.0068 0.9 0.013175 0.8 0.02601 0.7 0.03893 0.6 0.051255 0.5 0.06171 0.4 0.068425 0.3 0.06987 0.25 0.068085 0.2 0.064175 0.15 0.05797 0.1 0.048535 0.075 0.04199 0.05 0.034255 0.025 0.023885 0.0125 0.016745 0.01 0.01496 0.006 0.011645 0.004 0.009605 0.002 0.006375 0 0 0.0025 -0.008075 0.005 -0.010455 0.0075 -0.01258 0.01 -0.01377 0.0125 -0.01496 0.025 -0.0187 0.05 -0.023205 0.075 -0.025755 0.1 -0.02754 0.15 -0.029495 0.2 -0.03077 0.25 -0.031535 0.3 -0.032215 0.4 -0.03315 0.5 -0.03349 0.6 -0.03247 0.7 -0.02958 0.8 -0.024055 0.9 -0.015045 0.95 -0.00918 1 0 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for M6 (85%) (m685-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m685-il | 50,000 | 9 | 33.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 50,000 | 5 | 34.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 100,000 | 9 | 50.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 200,000 | 9 | 66.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 200,000 | 5 | 62.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 500,000 | 9 | 84.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 500,000 | 5 | 70.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 1,000,000 | 9 | 85.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 1,000,000 | 5 | 75.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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