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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 500,000
Max Cl/Cd: 116.57 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe394-il-500000.txt
Download as CSV file: xf-goe394-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3232   0.09918   0.09692  -0.0221   0.8951   0.0214
  -8.000  -0.3171   0.09612   0.09377  -0.0238   0.8703   0.0214
  -7.750  -0.3098   0.09169   0.08929  -0.0219   0.8580   0.0219
  -7.500  -0.2996   0.08918   0.08671  -0.0224   0.8463   0.0223
  -7.250  -0.2891   0.08670   0.08417  -0.0239   0.8369   0.0228
  -7.000  -0.2753   0.08385   0.08128  -0.0265   0.8296   0.0235
  -6.750  -0.2599   0.08075   0.07813  -0.0300   0.8232   0.0246
  -6.500  -0.2307   0.07648   0.07379  -0.0416   0.8173   0.0269
  -6.250  -0.2044   0.07232   0.06958  -0.0489   0.8124   0.0271
  -6.000  -0.1912   0.06692   0.06414  -0.0519   0.8081   0.0278
  -5.750  -0.1743   0.06470   0.06187  -0.0523   0.8036   0.0283
  -5.500  -0.1526   0.06221   0.05936  -0.0548   0.7984   0.0292
  -5.250  -0.1271   0.05928   0.05636  -0.0589   0.7936   0.0308
  -4.750  -0.0508   0.04882   0.04567  -0.0771   0.7859   0.0356
  -4.500  -0.0284   0.04710   0.04391  -0.0779   0.7819   0.0366
  -4.250  -0.0006   0.04491   0.04165  -0.0805   0.7782   0.0382
  -4.000   0.0574   0.03936   0.03581  -0.0920   0.7751   0.0436
  -3.750   0.0779   0.03650   0.03292  -0.0933   0.7721   0.0454
  -3.500   0.1044   0.03505   0.03143  -0.0944   0.7687   0.0470
  -3.250   0.1528   0.03176   0.02781  -0.1001   0.7653   0.0535
  -3.000   0.1982   0.01369   0.00805  -0.1096   0.7631   0.0394
  -2.750   0.2268   0.01249   0.00652  -0.1098   0.7598   0.0397
  -2.500   0.2554   0.01172   0.00556  -0.1098   0.7563   0.0403
  -2.250   0.2839   0.01118   0.00489  -0.1098   0.7527   0.0415
  -2.000   0.3123   0.01069   0.00427  -0.1097   0.7494   0.0422
  -1.750   0.3406   0.01031   0.00378  -0.1096   0.7461   0.0429
  -1.500   0.3688   0.01005   0.00343  -0.1095   0.7428   0.0435
  -1.250   0.3973   0.00962   0.00297  -0.1094   0.7392   0.0452
  -1.000   0.4256   0.00939   0.00273  -0.1093   0.7353   0.0476
  -0.750   0.4537   0.00924   0.00255  -0.1091   0.7313   0.0508
  -0.500   0.4819   0.00913   0.00247  -0.1090   0.7275   0.0595
  -0.250   0.5103   0.00925   0.00269  -0.1088   0.7230   0.0814
   0.000   0.5386   0.00947   0.00288  -0.1086   0.7181   0.0918
   0.250   0.5665   0.00966   0.00302  -0.1084   0.7136   0.0984
   0.500   0.5946   0.00962   0.00300  -0.1083   0.7083   0.1031
   0.750   0.6224   0.00955   0.00295  -0.1082   0.7025   0.1075
   1.000   0.6502   0.00956   0.00295  -0.1080   0.6970   0.1119
   1.250   0.6782   0.00945   0.00286  -0.1079   0.6901   0.1160
   1.500   0.7058   0.00931   0.00272  -0.1077   0.6835   0.1193
   1.750   0.7337   0.00917   0.00266  -0.1075   0.6750   0.1224
   2.000   0.7614   0.00910   0.00259  -0.1073   0.6658   0.1261
   2.250   0.7891   0.00899   0.00248  -0.1071   0.6528   0.1276
   2.500   0.8168   0.00883   0.00236  -0.1069   0.6343   0.1292
   2.750   0.8442   0.00871   0.00224  -0.1067   0.6070   0.1318
   3.000   0.8703   0.00880   0.00216  -0.1062   0.5608   0.1353
   3.250   0.8958   0.00910   0.00226  -0.1058   0.5234   0.1384
   3.500   0.9220   0.00934   0.00241  -0.1055   0.5007   0.1411
   3.750   0.9484   0.00956   0.00258  -0.1052   0.4816   0.1448
   4.000   0.9749   0.00976   0.00276  -0.1050   0.4651   0.1516
   4.250   1.0015   0.00992   0.00295  -0.1047   0.4513   0.1697
   4.500   1.0270   0.00881   0.00329  -0.1046   0.4396   1.0000
   4.750   1.0535   0.00905   0.00348  -0.1043   0.4278   1.0000
   5.250   1.1063   0.00952   0.00388  -0.1038   0.4029   1.0000
   5.500   1.1327   0.00973   0.00410  -0.1035   0.3906   1.0000
   5.750   1.1588   0.00999   0.00432  -0.1032   0.3749   1.0000
   6.000   1.1842   0.01030   0.00455  -0.1029   0.3518   1.0000
   6.250   1.2091   0.01067   0.00481  -0.1025   0.3234   1.0000
   6.500   1.2335   0.01110   0.00513  -0.1020   0.2919   1.0000
   6.750   1.2565   0.01171   0.00554  -0.1014   0.2491   1.0000
   7.000   1.2757   0.01282   0.00622  -0.1004   0.1763   1.0000
   7.250   1.2952   0.01386   0.00697  -0.0995   0.1297   1.0000
   7.500   1.3171   0.01456   0.00759  -0.0987   0.1104   1.0000
   7.750   1.3393   0.01518   0.00815  -0.0980   0.0918   1.0000
   8.000   1.3561   0.01646   0.00905  -0.0967   0.0435   1.0000
   8.250   1.3740   0.01756   0.01007  -0.0953   0.0286   1.0000
   8.500   1.3921   0.01859   0.01111  -0.0940   0.0240   1.0000
   8.750   1.4116   0.01936   0.01199  -0.0928   0.0222   1.0000
   9.000   1.4302   0.02018   0.01287  -0.0916   0.0205   1.0000
   9.250   1.4459   0.02122   0.01396  -0.0900   0.0189   1.0000
   9.500   1.4568   0.02265   0.01548  -0.0878   0.0177   1.0000
   9.750   1.4722   0.02354   0.01647  -0.0861   0.0169   1.0000
  10.000   1.4840   0.02460   0.01763  -0.0841   0.0162   1.0000
  10.250   1.4925   0.02575   0.01886  -0.0815   0.0156   1.0000
  10.500   1.4997   0.02703   0.02022  -0.0791   0.0151   1.0000
  10.750   1.5054   0.02850   0.02177  -0.0769   0.0146   1.0000
  11.000   1.5083   0.03033   0.02367  -0.0745   0.0142   1.0000
  11.250   1.5067   0.03273   0.02617  -0.0721   0.0137   1.0000
  11.500   1.5049   0.03536   0.02892  -0.0696   0.0134   1.0000
  11.750   1.5137   0.03690   0.03058  -0.0684   0.0131   1.0000
  12.000   1.5205   0.03867   0.03249  -0.0671   0.0127   1.0000
  12.250   1.5258   0.04067   0.03460  -0.0658   0.0123   1.0000
  12.500   1.5296   0.04287   0.03692  -0.0645   0.0120   1.0000
  12.750   1.5326   0.04518   0.03934  -0.0633   0.0117   1.0000
  13.000   1.5349   0.04762   0.04190  -0.0621   0.0115   1.0000
  13.250   1.5361   0.05020   0.04459  -0.0611   0.0113   1.0000
  13.500   1.5364   0.05291   0.04742  -0.0601   0.0110   1.0000
  13.750   1.5357   0.05577   0.05040  -0.0593   0.0108   1.0000
  14.000   1.5338   0.05882   0.05356  -0.0586   0.0107   1.0000
  14.250   1.5307   0.06209   0.05694  -0.0579   0.0105   1.0000
  14.500   1.5259   0.06566   0.06065  -0.0573   0.0104   1.0000
  14.750   1.5188   0.06961   0.06474  -0.0568   0.0103   1.0000
  15.000   1.5094   0.07409   0.06939  -0.0566   0.0102   1.0000
  15.250   1.4974   0.07908   0.07458  -0.0569   0.0101   1.0000
  15.500   1.4832   0.08462   0.08032  -0.0577   0.0101   1.0000
  15.750   1.4679   0.09061   0.08651  -0.0593   0.0100   1.0000
  16.000   1.4529   0.09678   0.09287  -0.0614   0.0100   1.0000
  16.250   1.4373   0.10337   0.09965  -0.0641   0.0100   1.0000
  16.500   1.4220   0.11020   0.10666  -0.0673   0.0100   1.0000
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