YS-930 (ys930-il)
YS-930 - YS930 hydrofoil (Shen / Eppler)
| Details | Dat file | Parser | |
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(ys930-il) YS-930 YS930 hydrofoil (Shen / Eppler) Max thickness 9.1% at 35% chord. Max camber 2.9% at 59.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
YS-930 1.00000 0.00000 0.99908 0.00015 0.99639 0.00070 0.99210 0.00177 0.98641 0.00335 0.97946 0.00537 0.97137 0.00771 0.96216 0.01022 0.95177 0.01281 0.94014 0.01548 0.92728 0.01831 0.91328 0.02132 0.89819 0.02450 0.88209 0.02786 0.86506 0.03136 0.84718 0.03500 0.82853 0.03874 0.80920 0.04256 0.78928 0.04640 0.76885 0.05022 0.74801 0.05393 0.72684 0.05748 0.70543 0.06067 0.68365 0.06330 0.66132 0.06547 0.63849 0.06731 0.61523 0.06884 0.59161 0.07008 0.56769 0.07105 0.54354 0.07175 0.51922 0.07219 0.49479 0.07237 0.47032 0.07230 0.44588 0.07199 0.42152 0.07144 0.39731 0.07066 0.37331 0.06965 0.34959 0.06842 0.32620 0.06697 0.30322 0.06532 0.28069 0.06347 0.25868 0.06144 0.23724 0.05922 0.21643 0.05684 0.19630 0.05430 0.17691 0.05161 0.15830 0.04880 0.14053 0.04586 0.12363 0.04282 0.10766 0.03969 0.09264 0.03648 0.07863 0.03321 0.06566 0.02991 0.05376 0.02658 0.04297 0.02325 0.03331 0.01994 0.02481 0.01668 0.01750 0.01348 0.01141 0.01039 0.00657 0.00742 0.00301 0.00459 0.00072 0.00198 0.00001 -0.00019 0.00102 -0.00234 0.00344 -0.00476 0.00720 -0.00723 0.01225 -0.00976 0.01854 -0.01231 0.02602 -0.01485 0.03466 -0.01734 0.04442 -0.01975 0.05527 -0.02204 0.06718 -0.02419 0.08010 -0.02615 0.09399 -0.02790 0.10881 -0.02937 0.12452 -0.03051 0.14109 -0.03116 0.15872 -0.03123 0.17755 -0.03090 0.19749 -0.03029 0.21847 -0.02946 0.24042 -0.02845 0.26327 -0.02730 0.28694 -0.02603 0.31136 -0.02467 0.33645 -0.02324 0.36212 -0.02177 0.38830 -0.02026 0.41490 -0.01875 0.44184 -0.01723 0.46902 -0.01573 0.49637 -0.01426 0.52379 -0.01283 0.55120 -0.01146 0.57850 -0.01014 0.60562 -0.00889 0.63246 -0.00771 0.65893 -0.00661 0.68496 -0.00560 0.71045 -0.00468 0.73533 -0.00385 0.75951 -0.00311 0.78292 -0.00246 0.80546 -0.00190 0.82708 -0.00143 0.84770 -0.00104 0.86724 -0.00073 0.88565 -0.00050 0.90285 -0.00032 0.91879 -0.00020 0.93341 -0.00011 0.94666 -0.00003 0.95850 0.00008 0.96897 0.00022 0.97806 0.00036 0.98571 0.00042 0.99183 0.00039 0.99633 0.00026 0.99907 0.00009 1.00000 0.00000 |
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Polars for YS-930 (ys930-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ys930-il | 50,000 | 9 | 24.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys930-il | 50,000 | 5 | 28.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys930-il | 100,000 | 9 | 42.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys930-il | 100,000 | 5 | 47.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys930-il | 200,000 | 9 | 77.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys930-il | 200,000 | 5 | 75.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys930-il | 500,000 | 9 | 119 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys930-il | 500,000 | 5 | 108.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys930-il | 1,000,000 | 9 | 155.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys930-il | 1,000,000 | 5 | 113.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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