DF102 (df102-il)
DF102 - David Fraser DF 102 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(df102-il) DF102 David Fraser DF 102 low Reynolds number airfoil Max thickness 11% at 29.1% chord. Max camber 2.4% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
DF102 1.00000 0.00000 0.99680 0.00043 0.98727 0.00187 0.97164 0.00435 0.95030 0.00793 0.92376 0.01258 0.89246 0.01818 0.85698 0.02450 0.81785 0.03123 0.77561 0.03809 0.73074 0.04484 0.68378 0.05129 0.63529 0.05731 0.58571 0.06279 0.53556 0.06757 0.48525 0.07149 0.43519 0.07436 0.38584 0.07605 0.33772 0.07652 0.29132 0.07580 0.24716 0.07397 0.20565 0.07144 0.16723 0.06830 0.13217 0.06431 0.10072 0.05920 0.07318 0.05270 0.04985 0.04470 0.03091 0.03506 0.01647 0.02449 0.00657 0.01426 0.00117 0.00554 0.00000 -0.00089 0.00488 -0.00767 0.01522 -0.01350 0.02996 -0.01893 0.04886 -0.02398 0.07201 -0.02849 0.09949 -0.03216 0.13137 -0.03475 0.16763 -0.03611 0.20790 -0.03629 0.25166 -0.03547 0.29840 -0.03397 0.34765 -0.03205 0.39889 -0.02988 0.45167 -0.02751 0.50538 -0.02496 0.55938 -0.02226 0.61299 -0.01953 0.66547 -0.01689 0.71621 -0.01444 0.76456 -0.01218 0.80992 -0.01004 0.85166 -0.00793 0.88919 -0.00585 0.92196 -0.00391 0.94944 -0.00229 0.97129 -0.00114 0.98715 -0.00046 0.99677 -0.00015 1.00000 -0.00007 |
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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 DF102 (df102-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| df102-il | 50,000 | 9 | 32.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 50,000 | 5 | 32.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 100,000 | 9 | 49.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 100,000 | 5 | 45.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 200,000 | 9 | 64.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 200,000 | 5 | 56.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 500,000 | 9 | 82.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 500,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| df102-il | 1,000,000 | 9 | 93.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| df102-il | 1,000,000 | 5 | 93 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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