FX 73-CL2-152 (fx73cl2152-il)
FX 73-CL2-152 - Wortmann FX 73-CL2-152 airfoil
| Details | Dat file | Parser | |
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(fx73cl2152-il) FX 73-CL2-152 Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord. Max camber 6.6% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 73-CL2-152 1.00000 0.00000 0.99893 0.00138 0.99572 0.00394 0.99039 0.00715 0.98296 0.01103 0.97347 0.01540 0.96194 0.02014 0.94844 0.02514 0.93301 0.03036 0.91573 0.03576 0.89668 0.04127 0.87592 0.04686 0.85355 0.05249 0.82967 0.05817 0.80438 0.06386 0.77779 0.06955 0.75000 0.07523 0.72114 0.08090 0.69134 0.08650 0.66072 0.09204 0.62941 0.09751 0.59755 0.10288 0.56526 0.10811 0.53270 0.11316 0.50000 0.11798 0.46730 0.12249 0.43474 0.12661 0.40245 0.13027 0.37059 0.13335 0.33928 0.13555 0.30866 0.13648 0.27886 0.13591 0.25000 0.13390 0.22221 0.13064 0.19562 0.12616 0.17033 0.12037 0.14645 0.11336 0.12408 0.10539 0.10332 0.09677 0.08427 0.08768 0.06699 0.07820 0.05156 0.06848 0.03806 0.05854 0.02653 0.04839 0.01704 0.03798 0.00961 0.02745 0.00428 0.01727 0.00107 0.00800 0.00000 0.00000 0.00107 -0.00697 0.00428 -0.01319 0.00961 -0.01865 0.01704 -0.02304 0.02653 -0.02623 0.03806 -0.02846 0.05156 -0.03003 0.06699 -0.03113 0.08427 -0.03174 0.10332 -0.03175 0.12408 -0.03102 0.14645 -0.02955 0.17033 -0.02739 0.19562 -0.02468 0.22221 -0.02153 0.25000 -0.01803 0.27886 -0.01431 0.30866 -0.01041 0.33928 -0.00637 0.37059 -0.00224 0.40245 0.00188 0.43474 0.00591 0.46730 0.00980 0.50000 0.01353 0.53270 0.01705 0.56526 0.02028 0.59755 0.02317 0.62941 0.02565 0.66072 0.02769 0.69134 0.02925 0.72114 0.03035 0.75000 0.03096 0.77779 0.03103 0.80438 0.03057 0.82967 0.02959 0.85355 0.02823 0.87592 0.02652 0.89668 0.02437 0.91573 0.02184 0.93301 0.01898 0.94844 0.01597 0.96194 0.01290 0.97347 0.00980 0.98296 0.00684 0.99039 0.00418 0.99572 0.00208 0.99893 0.00051 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 FX 73-CL2-152 (fx73cl2152-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73cl2152-il | 50,000 | 9 | 16.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 5 | 32.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 9 | 41.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 5 | 52.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 5 | 74.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 9 | 104.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 5 | 107.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 9 | 136.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 5 | 135.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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