MA409 (original) (modified line 7) (ma409-il)
MA409 (original) (modified line 7) - Michael Achterberg MA409 F1C class free flight airfoil (original)
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(ma409-il) MA409 (original) (modified line 7) Michael Achterberg MA409 F1C class free flight airfoil (original) Max thickness 6.8% at 25% chord. Max camber 3.3% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MA409 (original) (modified line 7) 1.00000 0.00070 0.95000 0.01246 0.90000 0.02308 0.80000 0.04015 0.70000 0.05236 0.60000 0.06154 0.55000 0.06543 0.50000 0.06945 0.45000 0.07186 0.40000 0.07391 0.35000 0.07434 0.30000 0.07398 0.25000 0.07302 0.20000 0.06925 0.15000 0.06421 0.10000 0.05673 0.07500 0.05132 0.05000 0.04479 0.02500 0.03500 0.01250 0.02831 0.00000 0.01749 0.01250 0.00878 0.02500 0.00437 0.05000 0.00082 0.07500 0.00022 0.10000 0.00000 0.15000 0.00122 0.20000 0.00280 0.25000 0.00514 0.30000 0.00789 0.35000 0.01031 0.40000 0.01229 0.45000 0.01424 0.50000 0.01499 0.55000 0.01525 0.60000 0.01536 0.70000 0.01384 0.80000 0.01107 0.90000 0.00704 0.95000 0.00355 1.00000 0.00000 |
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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 MA409 (original) (modified line 7) (ma409-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ma409-il | 50,000 | 9 | 42.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 50,000 | 5 | 42.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 100,000 | 9 | 61.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 100,000 | 5 | 59.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 200,000 | 9 | 81.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 200,000 | 5 | 72.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 500,000 | 9 | 99.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 500,000 | 5 | 89.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 1,000,000 | 9 | 110.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 1,000,000 | 5 | 94.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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