NACA6409 9% (n6409-il)
NACA6409 9% - NACA 6409
| Details | Dat file | Parser | |
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(n6409-il) NACA6409 9% NACA 6409 Max thickness 9% at 29.3% chord. Max camber 6% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
NACA6409 9% 1.00000 0.00000 0.99732 0.00084 0.98930 0.00333 0.97603 0.00737 0.95760 0.01284 0.93423 0.01954 0.90615 0.02724 0.87357 0.03571 0.83690 0.04464 0.79647 0.05378 0.75272 0.06283 0.70608 0.07153 0.65710 0.07961 0.60627 0.08684 0.55413 0.09302 0.50132 0.09796 0.44840 0.10152 0.39590 0.10360 0.34367 0.10352 0.29315 0.10086 0.24502 0.09584 0.19988 0.08874 0.15830 0.07992 0.12080 0.06982 0.08780 0.05889 0.05968 0.04762 0.03677 0.03646 0.01920 0.02581 0.00720 0.01603 0.00080 0.00737 0.00000 0.00000 0.00467 -0.00573 0.01467 -0.00956 0.02973 -0.01157 0.04970 -0.01192 0.07428 -0.01080 0.10317 -0.00844 0.13607 -0.00513 0.17257 -0.00119 0.21235 0.00307 0.25498 0.00729 0.30012 0.01112 0.34730 0.01425 0.39618 0.01639 0.44707 0.01772 0.49868 0.01871 0.55040 0.01925 0.60167 0.01929 0.65193 0.01880 0.70065 0.01780 0.74728 0.01634 0.79130 0.01451 0.83223 0.01241 0.86957 0.01017 0.90288 0.00791 0.93180 0.00576 0.95593 0.00383 0.97503 0.00221 0.98883 0.00101 0.99722 0.00025 1.00000 0.00000 |
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Polars for NACA6409 9% (n6409-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n6409-il | 50,000 | 9 | 27.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 50,000 | 5 | 36 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 9 | 61.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 5 | 63.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 9 | 87.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 5 | 87.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 9 | 122.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 5 | 118.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 9 | 151 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 5 | 144.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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