FX 74-130 WP1 (fx74130wp1-il)
FX 74-130 WP1 - Wortmann FX 74-130 WP1 airfoil
| Details | Dat file | Parser | |
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(fx74130wp1-il) FX 74-130 WP1 Wortmann FX 74-130 WP1 airfoil Max thickness 13% at 46.7% chord. Max camber 3.8% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
FX 74-130 WP1 1.00000 0.00000 0.99893 0.00051 0.99572 0.00169 0.99039 0.00328 0.98296 0.00531 0.97347 0.00776 0.96194 0.01066 0.94844 0.01406 0.93301 0.01794 0.91573 0.02232 0.89668 0.02729 0.87592 0.03286 0.85355 0.03902 0.82967 0.04568 0.80438 0.05284 0.77779 0.06055 0.75000 0.06850 0.72114 0.07606 0.69134 0.08272 0.66072 0.08829 0.62941 0.09301 0.59755 0.09694 0.56526 0.09991 0.53270 0.10187 0.50000 0.10290 0.46730 0.10318 0.43474 0.10278 0.40245 0.10170 0.37059 0.09999 0.33928 0.09768 0.30866 0.09481 0.27886 0.09142 0.25000 0.08755 0.22221 0.08323 0.19562 0.07850 0.17033 0.07342 0.14645 0.06802 0.12408 0.06235 0.10332 0.05646 0.08427 0.05042 0.06699 0.04428 0.05156 0.03808 0.03806 0.03192 0.02653 0.02589 0.01704 0.02003 0.00961 0.01450 0.00428 0.00923 0.00107 0.00426 0.00000 0.00000 0.00107 -0.00347 0.00428 -0.00616 0.00961 -0.00838 0.01704 -0.01051 0.02653 -0.01247 0.03806 -0.01428 0.05156 -0.01599 0.06699 -0.01755 0.08427 -0.01898 0.10332 -0.02030 0.12408 -0.02150 0.14645 -0.02260 0.17033 -0.02358 0.19562 -0.02445 0.22221 -0.02520 0.25000 -0.02584 0.27886 -0.02637 0.30866 -0.02679 0.33928 -0.02708 0.37059 -0.02725 0.40245 -0.02728 0.43474 -0.02719 0.46730 -0.02695 0.50000 -0.02657 0.53270 -0.02602 0.56526 -0.02530 0.59755 -0.02438 0.62941 -0.02322 0.66072 -0.02177 0.69134 -0.01997 0.72114 -0.01755 0.75000 -0.01433 0.77779 -0.01049 0.80438 -0.00657 0.82967 -0.00317 0.85355 -0.00050 0.87592 0.00151 0.89668 0.00290 0.91573 0.00372 0.93301 0.00405 0.94844 0.00400 0.96194 0.00364 0.97347 0.00305 0.98296 0.00234 0.99039 0.00160 0.99572 0.00093 0.99893 0.00032 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 74-130 WP1 (fx74130wp1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx74130wp1-il | 50,000 | 9 | 24.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 50,000 | 5 | 23.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 100,000 | 9 | 39.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 100,000 | 5 | 39.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 200,000 | 9 | 72 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 200,000 | 5 | 71.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 500,000 | 9 | 119.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 500,000 | 5 | 115.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74130wp1-il | 1,000,000 | 9 | 152.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74130wp1-il | 1,000,000 | 5 | 145.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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