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GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 591 AIRFOIL (goe591-il)
Reynolds number: 500,000
Max Cl/Cd: 103.08 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe591-il-500000-n5.txt
Download as CSV file: xf-goe591-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 591 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3102   0.12265   0.12029  -0.0390   1.0000   0.0087
 -10.000  -0.4906   0.02591   0.02257  -0.1140   0.9457   0.0138
  -9.750  -0.4750   0.02234   0.01847  -0.1149   0.9358   0.0145
  -9.500  -0.4461   0.02221   0.01835  -0.1153   0.9282   0.0150
  -9.250  -0.4154   0.02222   0.01836  -0.1160   0.9201   0.0155
  -9.000  -0.3885   0.02184   0.01789  -0.1162   0.9100   0.0161
  -8.750  -0.3639   0.02085   0.01668  -0.1163   0.8991   0.0169
  -8.500  -0.3423   0.01933   0.01481  -0.1160   0.8870   0.0179
  -8.250  -0.3196   0.01820   0.01336  -0.1155   0.8748   0.0186
  -8.000  -0.2949   0.01774   0.01282  -0.1152   0.8633   0.0192
  -7.750  -0.2688   0.01763   0.01265  -0.1149   0.8526   0.0198
  -7.500  -0.2433   0.01738   0.01228  -0.1146   0.8422   0.0205
  -7.250  -0.2187   0.01693   0.01168  -0.1141   0.8317   0.0214
  -7.000  -0.1945   0.01634   0.01090  -0.1135   0.8219   0.0223
  -6.750  -0.1697   0.01590   0.01026  -0.1130   0.8126   0.0231
  -6.500  -0.1443   0.01557   0.00977  -0.1125   0.8035   0.0237
  -6.250  -0.1211   0.01461   0.00861  -0.1119   0.7954   0.0246
  -6.000  -0.0965   0.01405   0.00795  -0.1114   0.7872   0.0254
  -5.750  -0.0710   0.01370   0.00751  -0.1109   0.7798   0.0262
  -5.500  -0.0454   0.01334   0.00706  -0.1105   0.7719   0.0270
  -5.250  -0.0198   0.01293   0.00653  -0.1101   0.7646   0.0277
  -5.000   0.0061   0.01258   0.00608  -0.1096   0.7566   0.0285
  -4.750   0.0319   0.01225   0.00564  -0.1092   0.7492   0.0293
  -4.500   0.0578   0.01190   0.00521  -0.1087   0.7410   0.0298
  -4.250   0.0837   0.01159   0.00479  -0.1083   0.7330   0.0302
  -4.000   0.1097   0.01131   0.00444  -0.1078   0.7245   0.0306
  -3.750   0.1358   0.01107   0.00412  -0.1074   0.7165   0.0309
  -3.500   0.1610   0.01069   0.00365  -0.1068   0.7075   0.0319
  -3.250   0.1867   0.01040   0.00331  -0.1063   0.6983   0.0330
  -3.000   0.2126   0.01020   0.00305  -0.1058   0.6894   0.0339
  -2.750   0.2388   0.01003   0.00283  -0.1054   0.6798   0.0346
  -2.500   0.2649   0.00991   0.00263  -0.1050   0.6701   0.0356
  -2.250   0.2908   0.00981   0.00247  -0.1045   0.6597   0.0365
  -2.000   0.3171   0.00972   0.00231  -0.1041   0.6494   0.0375
  -1.750   0.3433   0.00965   0.00219  -0.1037   0.6396   0.0388
  -1.500   0.3693   0.00961   0.00208  -0.1032   0.6291   0.0407
  -1.250   0.3953   0.00953   0.00200  -0.1028   0.6179   0.0475
  -1.000   0.4210   0.00945   0.00197  -0.1023   0.6071   0.0695
  -0.750   0.4469   0.00943   0.00193  -0.1019   0.5969   0.0821
  -0.500   0.4728   0.00943   0.00189  -0.1014   0.5858   0.0916
  -0.250   0.4985   0.00940   0.00188  -0.1010   0.5748   0.1076
   0.000   0.5240   0.00937   0.00188  -0.1005   0.5644   0.1353
   0.250   0.5493   0.00935   0.00191  -0.1000   0.5537   0.1701
   0.500   0.5750   0.00934   0.00193  -0.0996   0.5433   0.1983
   0.750   0.6003   0.00933   0.00197  -0.0992   0.5329   0.2341
   1.000   0.6232   0.00908   0.00205  -0.0984   0.5212   0.3735
   1.250   0.6365   0.00817   0.00219  -0.0956   0.5094   0.7572
   1.750   0.7399   0.00816   0.00244  -0.1059   0.4827   1.0000
   2.000   0.7630   0.00829   0.00251  -0.1049   0.4750   1.0000
   2.250   0.7862   0.00842   0.00258  -0.1040   0.4659   1.0000
   2.500   0.8092   0.00857   0.00266  -0.1030   0.4567   1.0000
   2.750   0.8320   0.00873   0.00276  -0.1020   0.4476   1.0000
   3.000   0.8556   0.00886   0.00285  -0.1011   0.4394   1.0000
   3.250   0.8783   0.00904   0.00296  -0.1001   0.4303   1.0000
   3.500   0.9020   0.00918   0.00308  -0.0993   0.4219   1.0000
   3.750   0.9251   0.00935   0.00320  -0.0984   0.4146   1.0000
   4.000   0.9491   0.00949   0.00333  -0.0977   0.4079   1.0000
   4.500   0.9962   0.00981   0.00362  -0.0961   0.3934   1.0000
   5.000   1.0427   0.01017   0.00394  -0.0944   0.3774   1.0000
   5.250   1.0652   0.01038   0.00412  -0.0935   0.3689   1.0000
   5.500   1.0885   0.01056   0.00430  -0.0927   0.3603   1.0000
   5.750   1.1109   0.01078   0.00449  -0.0917   0.3515   1.0000
   6.000   1.1325   0.01103   0.00472  -0.0906   0.3407   1.0000
   6.250   1.1548   0.01125   0.00493  -0.0897   0.3302   1.0000
   6.500   1.1740   0.01160   0.00520  -0.0882   0.3119   1.0000
   6.750   1.1921   0.01200   0.00551  -0.0866   0.2894   1.0000
   7.000   1.2080   0.01251   0.00587  -0.0846   0.2645   1.0000
   7.250   1.2242   0.01296   0.00624  -0.0827   0.2451   1.0000
   7.500   1.2390   0.01342   0.00662  -0.0805   0.2276   1.0000
   7.750   1.2529   0.01392   0.00704  -0.0782   0.2101   1.0000
   8.000   1.2665   0.01445   0.00750  -0.0759   0.1931   1.0000
   8.250   1.2796   0.01502   0.00799  -0.0736   0.1726   1.0000
   8.500   1.2883   0.01583   0.00863  -0.0706   0.1444   1.0000
   8.750   1.2963   0.01669   0.00935  -0.0677   0.1220   1.0000
   9.000   1.3064   0.01747   0.01006  -0.0652   0.1065   1.0000
   9.250   1.3165   0.01826   0.01081  -0.0628   0.0898   1.0000
   9.500   1.3117   0.01991   0.01219  -0.0586   0.0503   1.0000
   9.750   1.3100   0.02149   0.01364  -0.0550   0.0218   1.0000
  10.000   1.3170   0.02262   0.01477  -0.0527   0.0161   1.0000
  10.250   1.3271   0.02358   0.01579  -0.0509   0.0146   1.0000
  10.500   1.3354   0.02472   0.01700  -0.0490   0.0129   1.0000
  10.750   1.3458   0.02575   0.01810  -0.0474   0.0122   1.0000
  11.000   1.3555   0.02687   0.01931  -0.0459   0.0116   1.0000
  11.250   1.3639   0.02813   0.02065  -0.0444   0.0109   1.0000
  11.500   1.3708   0.02954   0.02213  -0.0428   0.0102   1.0000
  11.750   1.3764   0.03112   0.02379  -0.0414   0.0098   1.0000
  12.000   1.3791   0.03301   0.02577  -0.0399   0.0093   1.0000
  12.250   1.3853   0.03466   0.02751  -0.0387   0.0090   1.0000
  12.500   1.3907   0.03643   0.02937  -0.0377   0.0087   1.0000
  12.750   1.3947   0.03839   0.03142  -0.0367   0.0083   1.0000
  13.000   1.3976   0.04053   0.03366  -0.0359   0.0080   1.0000
  13.250   1.3993   0.04287   0.03609  -0.0351   0.0078   1.0000
  13.500   1.4008   0.04532   0.03863  -0.0345   0.0075   1.0000
  13.750   1.3993   0.04819   0.04159  -0.0341   0.0074   1.0000
  14.000   1.3984   0.05108   0.04458  -0.0338   0.0072   1.0000
  14.250   1.3947   0.05444   0.04804  -0.0337   0.0071   1.0000
  14.500   1.3888   0.05818   0.05188  -0.0339   0.0069   1.0000
  14.750   1.3830   0.06203   0.05584  -0.0342   0.0067   1.0000
  15.000   1.3789   0.06579   0.05971  -0.0346   0.0066   1.0000
  15.250   1.3763   0.06942   0.06345  -0.0352   0.0065   1.0000
  15.500   1.3739   0.07310   0.06723  -0.0359   0.0063   1.0000
  15.750   1.3655   0.07770   0.07195  -0.0368   0.0063   1.0000
  16.000   1.3623   0.08165   0.07602  -0.0377   0.0060   1.0000
  16.250   1.3568   0.08602   0.08049  -0.0389   0.0059   1.0000
  16.500   1.3519   0.09036   0.08493  -0.0401   0.0058   1.0000
  16.750   1.3442   0.09520   0.08988  -0.0415   0.0057   1.0000
  17.000   1.3401   0.09955   0.09432  -0.0430   0.0055   1.0000
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