Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il)
Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) - ATR 72 wing airfoil (from NTSB report)
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(atr72sm-il) Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) ATR 72 wing airfoil (from NTSB report) Max thickness 14.5% at 25.4% chord. Max camber 2.9% at 21.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) 1.00000 0.00000 0.96800 0.00510 0.94100 0.00977 0.91400 0.01481 0.88500 0.02050 0.85900 0.02570 0.83000 0.03144 0.80500 0.03625 0.77600 0.04158 0.75100 0.04597 0.72300 0.05070 0.69600 0.05512 0.67000 0.05926 0.64900 0.06250 0.62300 0.06632 0.59800 0.06982 0.57500 0.07294 0.55600 0.07548 0.53500 0.07826 0.51700 0.08058 0.48800 0.08411 0.45800 0.08735 0.43100 0.08989 0.40500 0.09206 0.38100 0.09390 0.33800 0.09688 0.29500 0.09936 0.25400 0.10086 0.21400 0.10082 0.19100 0.09974 0.15800 0.09629 0.13100 0.09133 0.10700 0.08492 0.08200 0.07581 0.06070 0.06560 0.03380 0.04802 0.02560 0.04107 0.00925 0.02284 0.00443 0.01503 0.00092 0.00636 0.00000 -0.00012 0.00450 -0.01216 0.01320 -0.01921 0.01660 -0.02105 0.05140 -0.03155 0.09150 -0.03704 0.13000 -0.03998 0.15700 -0.04137 0.18200 -0.04237 0.21500 -0.04342 0.24600 -0.04423 0.26800 -0.04470 0.29100 -0.04507 0.32100 -0.04531 0.34600 -0.04525 0.37600 -0.04486 0.40500 -0.04421 0.43400 -0.04337 0.46000 -0.04250 0.48700 -0.04149 0.51100 -0.04047 0.53200 -0.03948 0.55200 -0.03846 0.57200 -0.03736 0.59600 -0.03590 0.62400 -0.03399 0.65000 -0.03207 0.68200 -0.02957 0.71400 -0.02704 0.74300 -0.02477 0.76900 -0.02270 0.79600 -0.02044 0.82600 -0.01769 0.85400 -0.01486 0.88500 -0.01148 0.91600 -0.00795 0.94600 -0.00461 0.97900 -0.00143 1.00000 0.00000 |
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Similar airfoils
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Polars for Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program) (atr72sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| atr72sm-il | 50,000 | 9 | 20.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 50,000 | 5 | 25.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 100,000 | 9 | 33.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 100,000 | 5 | 39.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 200,000 | 9 | 48.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 200,000 | 5 | 55.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 500,000 | 9 | 77.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 500,000 | 5 | 81.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| atr72sm-il | 1,000,000 | 9 | 104.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| atr72sm-il | 1,000,000 | 5 | 105.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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