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YS-915 (ys915-il)

YS-915 - YS915 hydrofoil (Shen / Eppler)


Airfoil ys915-il
Details Dat file Parser  
(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)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ys915-il50,000920.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ys915-il50,000521.9 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ys915-il100,000929.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ys915-il100,000534 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ys915-il200,000954 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ys915-il200,000551.6 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ys915-il500,000991.9 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   ys915-il500,000573.7 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   ys915-il1,000,0009109.2 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   ys915-il1,000,000579.1 at α=1.5°Mach=0 Ncrit=5Xfoil predictionDetails
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