YS-915 (ys915-il)
YS-915 - YS915 hydrofoil (Shen / Eppler)
| Details | Dat file | Parser | |
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(ys915-il) YS-915 YS915 hydrofoil (Shen / Eppler) Max thickness 9.1% at 36.1% chord. Max camber 1.8% at 65.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
YS-915 1.00000 0.00000 0.99906 0.00009 0.99631 0.00048 0.99189 0.00128 0.98596 0.00254 0.97870 0.00420 0.97020 0.00619 0.96051 0.00840 0.94963 0.01075 0.93751 0.01324 0.92420 0.01594 0.90979 0.01886 0.89438 0.02198 0.87805 0.02530 0.86091 0.02876 0.84306 0.03232 0.82461 0.03591 0.80567 0.03943 0.78635 0.04265 0.76642 0.04532 0.74569 0.04762 0.72425 0.04966 0.70216 0.05146 0.67949 0.05304 0.65630 0.05440 0.63264 0.05556 0.60860 0.05651 0.58422 0.05726 0.55958 0.05781 0.53474 0.05816 0.50977 0.05832 0.48474 0.05828 0.45970 0.05806 0.43473 0.05765 0.40990 0.05705 0.38526 0.05628 0.36090 0.05533 0.33686 0.05422 0.31321 0.05294 0.29002 0.05150 0.26735 0.04991 0.24526 0.04817 0.22380 0.04630 0.20304 0.04430 0.18302 0.04218 0.16381 0.03995 0.14545 0.03762 0.12799 0.03520 0.11147 0.03270 0.09595 0.03014 0.08146 0.02752 0.06804 0.02486 0.05573 0.02218 0.04456 0.01948 0.03456 0.01679 0.02576 0.01413 0.01820 0.01151 0.01189 0.00896 0.00688 0.00651 0.00321 0.00418 0.00091 0.00195 0.00000 0.00005 0.00081 -0.00177 0.00325 -0.00390 0.00699 -0.00618 0.01203 -0.00852 0.01835 -0.01091 0.02592 -0.01333 0.03471 -0.01575 0.04467 -0.01816 0.05578 -0.02053 0.06801 -0.02284 0.08131 -0.02507 0.09564 -0.02721 0.11097 -0.02924 0.12725 -0.03113 0.14444 -0.03287 0.16247 -0.03444 0.18131 -0.03581 0.20090 -0.03696 0.22119 -0.03784 0.24210 -0.03840 0.26367 -0.03851 0.28602 -0.03820 0.30916 -0.03759 0.33300 -0.03677 0.35747 -0.03577 0.38248 -0.03463 0.40797 -0.03337 0.43384 -0.03202 0.46001 -0.03059 0.48641 -0.02911 0.51295 -0.02760 0.53954 -0.02606 0.56610 -0.02451 0.59255 -0.02296 0.61880 -0.02143 0.64477 -0.01992 0.67038 -0.01844 0.69554 -0.01701 0.72017 -0.01562 0.74420 -0.01428 0.76755 -0.01301 0.79014 -0.01179 0.81189 -0.01064 0.83275 -0.00955 0.85263 -0.00854 0.87147 -0.00758 0.88920 -0.00669 0.90578 -0.00585 0.92113 -0.00507 0.93520 -0.00432 0.94795 -0.00359 0.95935 -0.00283 0.96945 -0.00202 0.97827 -0.00126 0.98576 -0.00063 0.99181 -0.00021 0.99629 -0.00000 0.99906 0.00003 1.00000 0.00000 |
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Polars for YS-915 (ys915-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ys915-il | 50,000 | 9 | 20.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 50,000 | 5 | 21.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 100,000 | 9 | 29.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 100,000 | 5 | 34 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 200,000 | 9 | 54 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 200,000 | 5 | 51.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 500,000 | 9 | 91.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 500,000 | 5 | 73.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ys915-il | 1,000,000 | 9 | 109.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ys915-il | 1,000,000 | 5 | 79.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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