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YS-930 (ys930-il)

YS-930 - YS930 hydrofoil (Shen / Eppler)


Airfoil ys930-il
Details Dat file Parser  
(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)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   ys930-il50,000924.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ys930-il50,000528.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ys930-il100,000942.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   ys930-il100,000547.1 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ys930-il200,000977.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ys930-il200,000575.5 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ys930-il500,0009119 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   ys930-il500,0005108.2 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   ys930-il1,000,0009155.4 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   ys930-il1,000,0005113.3 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
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