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GOE 359 AIRFOIL (goe359-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 359 AIRFOIL (goe359-il)
Reynolds number: 1,000,000
Max Cl/Cd: 103.77 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe359-il-1000000-n5.txt
Download as CSV file: xf-goe359-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 359 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2288   0.09167   0.08958  -0.0421   0.8350   0.0039
  -8.250  -0.2231   0.08824   0.08610  -0.0438   0.8192   0.0039
  -8.000  -0.2176   0.08470   0.08251  -0.0458   0.8054   0.0040
  -7.750  -0.2096   0.08172   0.07949  -0.0478   0.7925   0.0041
  -7.500  -0.2003   0.07881   0.07654  -0.0503   0.7807   0.0042
  -7.250  -0.1866   0.07556   0.07326  -0.0539   0.7693   0.0043
  -7.000  -0.1711   0.07202   0.06967  -0.0582   0.7580   0.0045
  -6.750  -0.1536   0.06802   0.06562  -0.0633   0.7464   0.0047
  -6.500  -0.1333   0.06292   0.06046  -0.0701   0.7346   0.0051
  -6.250  -0.1039   0.05193   0.04936  -0.0852   0.7251   0.0061
  -6.000  -0.0770   0.04863   0.04596  -0.0899   0.7128   0.0065
  -5.750  -0.0481   0.04473   0.04194  -0.0951   0.7011   0.0069
  -5.500  -0.0020   0.02861   0.02525  -0.1114   0.6937   0.0090
  -5.250   0.0264   0.02528   0.02172  -0.1135   0.6829   0.0100
  -5.000   0.0536   0.01523   0.01068  -0.1168   0.6747   0.0127
  -4.750   0.0810   0.01534   0.01076  -0.1167   0.6631   0.0138
  -4.500   0.1067   0.01224   0.00706  -0.1170   0.6531   0.0177
  -4.250   0.1342   0.01215   0.00686  -0.1169   0.6416   0.0181
  -3.750   0.1895   0.01235   0.00695  -0.1167   0.6200   0.0194
  -3.500   0.2171   0.01254   0.00710  -0.1166   0.6109   0.0200
  -3.000   0.2720   0.01235   0.00672  -0.1165   0.5884   0.0217
  -2.750   0.2994   0.01198   0.00620  -0.1164   0.5754   0.0225
  -2.500   0.3269   0.01152   0.00559  -0.1163   0.5632   0.0232
  -2.250   0.3544   0.01101   0.00491  -0.1162   0.5524   0.0236
  -2.000   0.3819   0.01068   0.00446  -0.1161   0.5418   0.0243
  -1.750   0.4095   0.01029   0.00395  -0.1160   0.5311   0.0248
  -1.500   0.4370   0.01003   0.00359  -0.1159   0.5200   0.0253
  -1.250   0.4645   0.00989   0.00337  -0.1158   0.5091   0.0259
  -1.000   0.4920   0.00984   0.00324  -0.1157   0.4982   0.0264
  -0.750   0.5196   0.00982   0.00317  -0.1156   0.4878   0.0267
  -0.500   0.5469   0.00957   0.00283  -0.1155   0.4773   0.0274
  -0.250   0.5740   0.00921   0.00239  -0.1154   0.4671   0.0284
   0.000   0.6015   0.00906   0.00220  -0.1153   0.4576   0.0290
   0.250   0.6287   0.00899   0.00207  -0.1152   0.4457   0.0293
   0.500   0.6558   0.00897   0.00198  -0.1151   0.4316   0.0296
   0.750   0.6830   0.00895   0.00190  -0.1149   0.4218   0.0298
   1.000   0.7105   0.00893   0.00185  -0.1149   0.4123   0.0303
   1.250   0.7377   0.00895   0.00182  -0.1147   0.4010   0.0308
   1.500   0.7648   0.00898   0.00179  -0.1146   0.3902   0.0308
   1.750   0.7921   0.00901   0.00178  -0.1145   0.3806   0.0308
   2.000   0.8194   0.00905   0.00178  -0.1144   0.3706   0.0308
   2.250   0.8462   0.00915   0.00181  -0.1143   0.3553   0.0310
   2.500   0.8721   0.00934   0.00188  -0.1140   0.3292   0.0314
   2.750   0.8965   0.00973   0.00204  -0.1135   0.2846   0.0323
   3.000   0.9211   0.01010   0.00224  -0.1130   0.2504   0.0345
   3.250   0.9467   0.01034   0.00241  -0.1127   0.2325   0.0391
   3.750   0.9980   0.01073   0.00283  -0.1122   0.1986   0.1500
   4.000   1.0201   0.00983   0.00327  -0.1118   0.1788   0.8584
   4.500   1.0606   0.01130   0.00429  -0.1094   0.0572   1.0000
   4.750   1.0859   0.01158   0.00453  -0.1090   0.0505   1.0000
   5.000   1.1113   0.01184   0.00476  -0.1087   0.0445   1.0000
   5.250   1.1343   0.01235   0.00516  -0.1080   0.0204   1.0000
   5.500   1.1591   0.01266   0.00544  -0.1076   0.0137   1.0000
   5.750   1.1841   0.01293   0.00574  -0.1072   0.0118   1.0000
   6.000   1.2087   0.01325   0.00608  -0.1067   0.0101   1.0000
   6.250   1.2328   0.01359   0.00648  -0.1062   0.0086   1.0000
   6.500   1.2571   0.01391   0.00680  -0.1057   0.0076   1.0000
   6.750   1.2808   0.01426   0.00718  -0.1051   0.0068   1.0000
   7.000   1.3037   0.01470   0.00766  -0.1044   0.0060   1.0000
   7.250   1.3268   0.01508   0.00809  -0.1038   0.0056   1.0000
   7.500   1.3496   0.01548   0.00851  -0.1031   0.0051   1.0000
   7.750   1.3720   0.01589   0.00893  -0.1024   0.0046   1.0000
   8.000   1.3928   0.01643   0.00951  -0.1014   0.0041   1.0000
   8.250   1.4131   0.01700   0.01014  -0.1003   0.0039   1.0000
   8.500   1.4333   0.01755   0.01074  -0.0992   0.0037   1.0000
   8.750   1.4523   0.01815   0.01142  -0.0980   0.0035   1.0000
   9.000   1.4706   0.01878   0.01211  -0.0967   0.0032   1.0000
   9.250   1.4881   0.01944   0.01282  -0.0953   0.0031   1.0000
   9.500   1.5045   0.02012   0.01355  -0.0937   0.0029   1.0000
   9.750   1.5187   0.02082   0.01431  -0.0918   0.0028   1.0000
  10.000   1.5273   0.02177   0.01533  -0.0890   0.0026   1.0000
  10.250   1.5350   0.02279   0.01644  -0.0862   0.0025   1.0000
  10.500   1.5442   0.02374   0.01747  -0.0838   0.0024   1.0000
  10.750   1.5514   0.02488   0.01871  -0.0813   0.0023   1.0000
  11.000   1.5564   0.02626   0.02021  -0.0790   0.0022   1.0000
  11.250   1.5595   0.02792   0.02197  -0.0767   0.0022   1.0000
  11.500   1.5617   0.02979   0.02395  -0.0748   0.0021   1.0000
  11.750   1.5634   0.03188   0.02615  -0.0732   0.0020   1.0000
  12.000   1.5639   0.03421   0.02858  -0.0719   0.0020   1.0000
  12.250   1.5635   0.03677   0.03125  -0.0708   0.0019   1.0000
  12.500   1.5626   0.03950   0.03408  -0.0699   0.0019   1.0000
  12.750   1.5610   0.04242   0.03710  -0.0693   0.0018   1.0000
  13.000   1.5592   0.04549   0.04027  -0.0688   0.0018   1.0000
  13.250   1.5556   0.04881   0.04371  -0.0685   0.0018   1.0000
  13.500   1.5523   0.05222   0.04721  -0.0684   0.0017   1.0000
  13.750   1.5483   0.05578   0.05088  -0.0685   0.0017   1.0000
  14.000   1.5441   0.05942   0.05462  -0.0686   0.0017   1.0000
  14.250   1.5367   0.06361   0.05891  -0.0689   0.0017   1.0000
  14.500   1.5307   0.06773   0.06313  -0.0694   0.0016   1.0000
  14.750   1.5223   0.07225   0.06776  -0.0700   0.0016   1.0000
  15.000   1.5162   0.07657   0.07217  -0.0708   0.0016   1.0000
  15.250   1.5069   0.08140   0.07711  -0.0717   0.0016   1.0000
  15.500   1.4969   0.08643   0.08227  -0.0727   0.0015   1.0000
  15.750   1.4863   0.09155   0.08750  -0.0738   0.0015   1.0000
  16.000   1.4741   0.09697   0.09303  -0.0750   0.0015   1.0000
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