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YS-930 (ys930-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: YS-930 (ys930-il)
Reynolds number: 500,000
Max Cl/Cd: 118.95 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ys930-il-500000.txt
Download as CSV file: xf-ys930-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: YS-930                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3107   0.10582   0.10373  -0.0539   0.9942   0.0186
 -11.000  -0.3065   0.10089   0.09880  -0.0568   0.9924   0.0197
  -7.250  -0.3314   0.02327   0.01870  -0.1194   0.9336   0.0112
  -7.000  -0.3156   0.01975   0.01473  -0.1184   0.9288   0.0104
  -6.750  -0.2959   0.01747   0.01214  -0.1172   0.9244   0.0100
  -6.500  -0.2733   0.01572   0.01015  -0.1165   0.9212   0.0098
  -6.250  -0.2491   0.01432   0.00855  -0.1160   0.9186   0.0100
  -6.000  -0.2284   0.01333   0.00741  -0.1148   0.9148   0.0107
  -5.750  -0.2040   0.01274   0.00672  -0.1142   0.9116   0.0120
  -5.500  -0.1829   0.01137   0.00510  -0.1132   0.9087   0.0170
  -5.250  -0.1569   0.01079   0.00441  -0.1130   0.9067   0.0259
  -5.000  -0.1330   0.00990   0.00370  -0.1125   0.9046   0.0775
  -4.750  -0.1107   0.00933   0.00353  -0.1120   0.9021   0.1831
  -4.500  -0.0840   0.00928   0.00347  -0.1119   0.9000   0.2038
  -4.250  -0.0568   0.00925   0.00338  -0.1120   0.8980   0.2165
  -4.000  -0.0292   0.00919   0.00326  -0.1121   0.8961   0.2270
  -3.750  -0.0011   0.00918   0.00323  -0.1123   0.8945   0.2433
  -3.500   0.0269   0.00911   0.00316  -0.1125   0.8931   0.2534
  -3.250   0.0549   0.00903   0.00306  -0.1127   0.8918   0.2607
  -3.000   0.0807   0.00900   0.00301  -0.1124   0.8900   0.2679
  -2.750   0.1063   0.00892   0.00294  -0.1122   0.8879   0.2752
  -2.250   0.1593   0.00881   0.00285  -0.1120   0.8843   0.2940
  -2.000   0.1864   0.00873   0.00282  -0.1120   0.8826   0.3079
  -1.750   0.2138   0.00865   0.00279  -0.1120   0.8812   0.3257
  -1.500   0.2414   0.00856   0.00278  -0.1122   0.8798   0.3500
  -1.250   0.2692   0.00847   0.00280  -0.1124   0.8785   0.3833
  -1.000   0.2937   0.00839   0.00288  -0.1119   0.8766   0.4252
  -0.750   0.3179   0.00828   0.00297  -0.1114   0.8743   0.4776
  -0.500   0.3425   0.00814   0.00306  -0.1109   0.8721   0.5410
  -0.250   0.3671   0.00796   0.00314  -0.1104   0.8700   0.6188
   0.000   0.3912   0.00773   0.00323  -0.1096   0.8680   0.7105
   0.250   0.4148   0.00748   0.00332  -0.1085   0.8661   0.8139
   0.500   0.4535   0.00731   0.00345  -0.1105   0.8650   0.9246
   0.750   0.5061   0.00730   0.00349  -0.1161   0.8636   0.9717
   1.000   0.5473   0.00731   0.00354  -0.1191   0.8604   0.9907
   1.250   0.5926   0.00724   0.00351  -0.1231   0.8569   1.0000
   1.500   0.6199   0.00719   0.00344  -0.1228   0.8524   1.0000
   1.750   0.6412   0.00720   0.00348  -0.1213   0.8458   1.0000
   2.000   0.6687   0.00708   0.00334  -0.1209   0.8387   1.0000
   2.250   0.6899   0.00698   0.00328  -0.1192   0.8285   1.0000
   2.500   0.7135   0.00676   0.00303  -0.1177   0.8129   1.0000
   2.750   0.7337   0.00661   0.00287  -0.1156   0.7951   1.0000
   3.000   0.7542   0.00655   0.00285  -0.1138   0.7797   1.0000
   3.250   0.7732   0.00650   0.00280  -0.1116   0.7554   1.0000
   3.500   0.7777   0.00670   0.00260  -0.1060   0.6466   1.0000
   3.750   0.7643   0.00803   0.00307  -0.0973   0.4827   1.0000
   4.000   0.7576   0.00943   0.00368  -0.0907   0.3181   1.0000
   4.250   0.7554   0.01096   0.00434  -0.0852   0.1421   1.0000
   4.500   0.7609   0.01229   0.00504  -0.0812   0.0282   1.0000
   4.750   0.7737   0.01332   0.00617  -0.0780   0.0134   1.0000
   5.000   0.7913   0.01395   0.00687  -0.0759   0.0120   1.0000
   5.250   0.8066   0.01474   0.00774  -0.0733   0.0111   1.0000
   5.500   0.8214   0.01568   0.00877  -0.0707   0.0107   1.0000
   5.750   0.8384   0.01686   0.01004  -0.0685   0.0106   1.0000
   6.000   0.8633   0.01847   0.01176  -0.0679   0.0108   1.0000
   6.250   0.8912   0.01991   0.01330  -0.0678   0.0103   1.0000
   6.500   0.9107   0.02022   0.01361  -0.0666   0.0087   1.0000
   6.750   0.9411   0.02215   0.01570  -0.0670   0.0086   1.0000
   7.000   0.9676   0.02414   0.01788  -0.0668   0.0080   1.0000
   7.250   1.0060   0.03290   0.02747  -0.0656   0.0149   1.0000
   7.500   1.0184   0.03601   0.03081  -0.0633   0.0142   1.0000
   7.750   1.0035   0.04526   0.04066  -0.0575   0.0131   1.0000
   8.000   1.0071   0.04831   0.04397  -0.0539   0.0131   1.0000
   8.250   1.0086   0.05130   0.04722  -0.0502   0.0130   1.0000
   8.500   1.0075   0.05414   0.05032  -0.0463   0.0130   1.0000
   8.750   1.0042   0.05679   0.05320  -0.0423   0.0129   1.0000
   9.000   1.0175   0.05668   0.05330  -0.0391   0.0119   1.0000
   9.250   1.0145   0.05930   0.05611  -0.0352   0.0113   1.0000
   9.500   1.0028   0.06203   0.05901  -0.0305   0.0110   1.0000
   9.750   0.9875   0.06510   0.06223  -0.0263   0.0108   1.0000
  10.000   0.9706   0.06839   0.06568  -0.0230   0.0107   1.0000
  10.250   0.9527   0.07196   0.06938  -0.0207   0.0107   1.0000
  10.500   0.9324   0.07616   0.07370  -0.0193   0.0107   1.0000
  10.750   0.9111   0.08091   0.07857  -0.0191   0.0109   1.0000
  11.000   0.8897   0.08648   0.08424  -0.0205   0.0110   1.0000
  11.250   0.8677   0.09286   0.09071  -0.0235   0.0115   1.0000
  11.500   0.8468   0.10120   0.09911  -0.0289   0.0118   1.0000
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