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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 500,000
Max Cl/Cd: 91.94 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe240-il-500000-n5.txt
Download as CSV file: xf-goe240-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3295   0.10740   0.10512  -0.0247   1.0000   0.0073
  -9.250  -0.3256   0.10387   0.10162  -0.0260   1.0000   0.0074
  -9.000  -0.3241   0.09996   0.09773  -0.0273   1.0000   0.0077
  -8.750  -0.3176   0.09808   0.09588  -0.0276   1.0000   0.0080
  -8.500  -0.3098   0.09588   0.09370  -0.0286   0.9986   0.0083
  -8.250  -0.2951   0.09245   0.09027  -0.0322   0.9930   0.0087
  -8.000  -0.2812   0.08842   0.08625  -0.0364   0.9861   0.0088
  -7.750  -0.2689   0.08446   0.08229  -0.0403   0.9775   0.0089
  -7.500  -0.2564   0.08052   0.07835  -0.0445   0.9676   0.0091
  -7.250  -0.2420   0.07631   0.07413  -0.0494   0.9566   0.0093
  -7.000  -0.2272   0.07176   0.06956  -0.0546   0.9426   0.0097
  -6.750  -0.2106   0.06514   0.06289  -0.0625   0.9218   0.0105
  -6.500  -0.1922   0.06312   0.06078  -0.0646   0.8886   0.0109
  -6.250  -0.1732   0.06065   0.05816  -0.0671   0.8562   0.0114
  -6.000  -0.1507   0.05688   0.05422  -0.0716   0.8362   0.0119
  -5.750  -0.1241   0.05208   0.04926  -0.0777   0.8230   0.0126
  -5.500  -0.0895   0.04415   0.04108  -0.0871   0.8131   0.0143
  -5.250  -0.0650   0.04298   0.03982  -0.0884   0.8042   0.0148
  -5.000  -0.0369   0.04015   0.03684  -0.0914   0.7965   0.0157
  -4.750   0.0043   0.02936   0.02550  -0.0995   0.7912   0.0187
  -4.500   0.0302   0.02862   0.02469  -0.1002   0.7854   0.0192
  -4.250   0.0571   0.02724   0.02316  -0.1010   0.7802   0.0198
  -4.000   0.0859   0.02447   0.02014  -0.1022   0.7755   0.0209
  -3.750   0.1165   0.01927   0.01437  -0.1035   0.7707   0.0232
  -3.500   0.1450   0.01706   0.01170  -0.1038   0.7657   0.0240
  -3.250   0.1725   0.01507   0.00931  -0.1041   0.7611   0.0250
  -3.000   0.2001   0.01414   0.00823  -0.1043   0.7552   0.0257
  -2.750   0.2277   0.01337   0.00727  -0.1043   0.7485   0.0262
  -2.500   0.2555   0.01269   0.00644  -0.1043   0.7413   0.0267
  -2.250   0.2833   0.01213   0.00572  -0.1043   0.7339   0.0271
  -2.000   0.3112   0.01161   0.00509  -0.1042   0.7269   0.0275
  -1.750   0.3389   0.01117   0.00452  -0.1041   0.7187   0.0278
  -1.500   0.3667   0.01080   0.00407  -0.1040   0.7096   0.0283
  -1.250   0.3943   0.01050   0.00368  -0.1039   0.7007   0.0289
  -1.000   0.4222   0.01016   0.00328  -0.1038   0.6920   0.0291
  -0.750   0.4499   0.00987   0.00293  -0.1037   0.6837   0.0292
  -0.500   0.4776   0.00963   0.00264  -0.1036   0.6728   0.0294
  -0.250   0.5050   0.00945   0.00239  -0.1034   0.6571   0.0297
   0.000   0.5323   0.00931   0.00218  -0.1032   0.6367   0.0302
   0.250   0.5591   0.00926   0.00201  -0.1029   0.6118   0.0308
   0.500   0.5856   0.00928   0.00190  -0.1026   0.5821   0.0313
   0.750   0.6116   0.00940   0.00185  -0.1022   0.5510   0.0318
   1.000   0.6379   0.00952   0.00183  -0.1019   0.5260   0.0322
   1.500   0.6916   0.00966   0.00181  -0.1016   0.4940   0.0344
   1.750   0.7187   0.00972   0.00183  -0.1014   0.4797   0.0365
   2.000   0.7450   0.00989   0.00189  -0.1012   0.4521   0.0379
   2.250   0.7704   0.01016   0.00197  -0.1008   0.4082   0.0394
   2.750   0.8209   0.01074   0.00229  -0.1001   0.3361   0.0785
   3.000   0.8469   0.01096   0.00245  -0.0998   0.3166   0.0913
   3.250   0.8729   0.01105   0.00266  -0.0997   0.3001   0.1784
   3.750   0.9212   0.01002   0.00313  -0.0987   0.2680   1.0000
   4.000   0.9469   0.01030   0.00332  -0.0984   0.2481   1.0000
   4.250   0.9718   0.01066   0.00354  -0.0980   0.2222   1.0000
   4.500   0.9961   0.01110   0.00381  -0.0975   0.1916   1.0000
   4.750   1.0204   0.01152   0.00410  -0.0970   0.1691   1.0000
   5.000   1.0452   0.01187   0.00438  -0.0966   0.1554   1.0000
   5.250   1.0702   0.01219   0.00466  -0.0962   0.1446   1.0000
   5.500   1.0945   0.01257   0.00496  -0.0957   0.1307   1.0000
   5.750   1.1184   0.01299   0.00530  -0.0952   0.1151   1.0000
   6.000   1.1424   0.01339   0.00563  -0.0947   0.1009   1.0000
   6.250   1.1628   0.01418   0.00617  -0.0937   0.0604   1.0000
   6.500   1.1859   0.01465   0.00662  -0.0931   0.0532   1.0000
   6.750   1.2099   0.01499   0.00702  -0.0925   0.0485   1.0000
   7.000   1.2331   0.01542   0.00746  -0.0919   0.0424   1.0000
   7.250   1.2538   0.01609   0.00802  -0.0909   0.0195   1.0000
   7.500   1.2751   0.01670   0.00862  -0.0900   0.0139   1.0000
   7.750   1.2974   0.01717   0.00915  -0.0892   0.0125   1.0000
   8.000   1.3189   0.01770   0.00978  -0.0882   0.0113   1.0000
   8.250   1.3391   0.01834   0.01050  -0.0871   0.0100   1.0000
   8.500   1.3576   0.01912   0.01138  -0.0858   0.0088   1.0000
   8.750   1.3775   0.01970   0.01204  -0.0847   0.0083   1.0000
   9.000   1.3961   0.02038   0.01280  -0.0834   0.0078   1.0000
   9.250   1.4136   0.02112   0.01364  -0.0819   0.0074   1.0000
   9.500   1.4297   0.02192   0.01452  -0.0803   0.0070   1.0000
   9.750   1.4436   0.02280   0.01548  -0.0784   0.0066   1.0000
  10.000   1.4524   0.02387   0.01663  -0.0757   0.0063   1.0000
  10.250   1.4589   0.02510   0.01797  -0.0728   0.0060   1.0000
  10.500   1.4699   0.02603   0.01899  -0.0707   0.0057   1.0000
  10.750   1.4790   0.02712   0.02018  -0.0684   0.0054   1.0000
  11.000   1.4857   0.02843   0.02162  -0.0661   0.0052   1.0000
  11.250   1.4911   0.02990   0.02320  -0.0639   0.0050   1.0000
  11.500   1.4954   0.03154   0.02494  -0.0618   0.0049   1.0000
  11.750   1.4993   0.03332   0.02683  -0.0600   0.0047   1.0000
  12.000   1.5020   0.03532   0.02894  -0.0584   0.0046   1.0000
  12.250   1.5041   0.03749   0.03123  -0.0571   0.0045   1.0000
  12.500   1.5051   0.03989   0.03373  -0.0560   0.0044   1.0000
  12.750   1.5043   0.04256   0.03651  -0.0551   0.0043   1.0000
  13.000   1.5016   0.04556   0.03963  -0.0543   0.0042   1.0000
  13.250   1.4961   0.04896   0.04315  -0.0537   0.0041   1.0000
  13.500   1.4882   0.05280   0.04713  -0.0533   0.0041   1.0000
  13.750   1.4776   0.05708   0.05155  -0.0532   0.0040   1.0000
  14.000   1.4712   0.06103   0.05564  -0.0533   0.0040   1.0000
  14.250   1.4653   0.06512   0.05987  -0.0538   0.0039   1.0000
  14.500   1.4588   0.06942   0.06431  -0.0545   0.0039   1.0000
  14.750   1.4514   0.07398   0.06901  -0.0554   0.0038   1.0000
  15.000   1.4436   0.07875   0.07392  -0.0565   0.0038   1.0000
  15.250   1.4354   0.08370   0.07901  -0.0578   0.0038   1.0000
  15.500   1.4267   0.08879   0.08424  -0.0592   0.0037   1.0000
  15.750   1.4177   0.09406   0.08965  -0.0609   0.0037   1.0000
  16.000   1.4085   0.09949   0.09522  -0.0627   0.0036   1.0000
  16.250   1.3992   0.10503   0.10090  -0.0647   0.0036   1.0000
  16.500   1.3895   0.11075   0.10674  -0.0669   0.0035   1.0000
  16.750   1.3801   0.11655   0.11268  -0.0693   0.0035   1.0000
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