YS-900 (ys900-il)
YS-900 - YS900 hyrdofoil (Shen / Eppler)
| Details | Dat file | Parser | |
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(ys900-il) YS-900 YS900 hyrdofoil (Shen / Eppler) Max thickness 9% at 52.5% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
YS-900 1.00000 0.00000 0.99898 0.00004 0.99600 0.00033 0.99120 0.00103 0.98481 0.00222 0.97701 0.00390 0.96796 0.00599 0.95777 0.00839 0.94647 0.01102 0.93409 0.01386 0.92072 0.01695 0.90653 0.02020 0.89166 0.02354 0.87627 0.02664 0.86007 0.02919 0.84278 0.03140 0.82451 0.03341 0.80532 0.03523 0.78527 0.03688 0.76440 0.03837 0.74279 0.03971 0.72049 0.04089 0.69756 0.04192 0.67406 0.04280 0.65006 0.04354 0.62563 0.04413 0.60084 0.04457 0.57574 0.04486 0.55041 0.04502 0.52491 0.04503 0.49932 0.04490 0.47371 0.04463 0.44815 0.04422 0.42270 0.04368 0.39743 0.04301 0.37241 0.04221 0.34772 0.04129 0.32341 0.04024 0.29956 0.03909 0.27622 0.03782 0.25347 0.03645 0.23136 0.03498 0.20996 0.03341 0.18931 0.03176 0.16948 0.03003 0.15053 0.02823 0.13250 0.02637 0.11544 0.02444 0.09940 0.02248 0.08442 0.02047 0.07055 0.01844 0.05781 0.01638 0.04626 0.01433 0.03592 0.01228 0.02682 0.01025 0.01899 0.00827 0.01245 0.00633 0.00723 0.00449 0.00336 0.00275 0.00088 0.00119 0.00000 0.00000 0.00088 -0.00119 0.00336 -0.00275 0.00723 -0.00449 0.01245 -0.00633 0.01899 -0.00827 0.02682 -0.01025 0.03592 -0.01228 0.04626 -0.01433 0.05781 -0.01638 0.07055 -0.01844 0.08442 -0.02047 0.09940 -0.02248 0.11544 -0.02444 0.13250 -0.02637 0.15053 -0.02823 0.16948 -0.03003 0.18931 -0.03176 0.20996 -0.03341 0.23136 -0.03498 0.25347 -0.03645 0.27622 -0.03782 0.29956 -0.03909 0.32341 -0.04024 0.34772 -0.04129 0.37241 -0.04221 0.39743 -0.04301 0.42270 -0.04368 0.44815 -0.04422 0.47371 -0.04463 0.49932 -0.04490 0.52491 -0.04503 0.55041 -0.04502 0.57574 -0.04486 0.60084 -0.04457 0.62563 -0.04413 0.65006 -0.04354 0.67406 -0.04280 0.69756 -0.04192 0.72049 -0.04089 0.74279 -0.03971 0.76440 -0.03837 0.78527 -0.03688 0.80532 -0.03523 0.82451 -0.03341 0.84278 -0.03140 0.86007 -0.02919 0.87627 -0.02664 0.89166 -0.02354 0.90653 -0.02020 0.92072 -0.01695 0.93409 -0.01386 0.94647 -0.01102 0.95777 -0.00839 0.96796 -0.00599 0.97701 -0.00390 0.98481 -0.00222 0.99120 -0.00103 0.99600 -0.00033 0.99898 -0.00004 1.00000 0.000 |
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Polars for YS-900 (ys900-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ys900-il | 50,000 | 9 | 17.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys900-il | 50,000 | 5 | 17.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys900-il | 100,000 | 9 | 21 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys900-il | 100,000 | 5 | 21.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys900-il | 200,000 | 9 | 21.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys900-il | 200,000 | 5 | 21.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys900-il | 500,000 | 9 | 24.2 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys900-il | 500,000 | 5 | 33.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys900-il | 1,000,000 | 9 | 22.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys900-il | 1,000,000 | 5 | 49 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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