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GOE 612 AIRFOIL (goe612-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 612 AIRFOIL (goe612-il)
Reynolds number: 200,000
Max Cl/Cd: 74.73 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe612-il-200000.txt
Download as CSV file: xf-goe612-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 612 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1415   0.09088   0.08725  -0.0819   0.9682   0.0936
  -9.000  -0.1219   0.08826   0.08463  -0.0836   0.9614   0.0958
  -8.750  -0.1822   0.03864   0.03487  -0.1247   0.9283   0.0727
  -8.500  -0.1439   0.03828   0.03458  -0.1250   0.9253   0.0737
  -8.250  -0.3014   0.03418   0.02854  -0.1266   0.9093   0.0644
  -8.000  -0.2902   0.03185   0.02586  -0.1251   0.9001   0.0644
  -7.750  -0.2693   0.02981   0.02359  -0.1249   0.8939   0.0648
  -7.500  -0.2401   0.02835   0.02201  -0.1256   0.8905   0.0659
  -7.250  -0.2256   0.02734   0.02087  -0.1236   0.8805   0.0668
  -7.000  -0.1998   0.02591   0.01921  -0.1235   0.8756   0.0679
  -6.750  -0.1759   0.02454   0.01759  -0.1229   0.8702   0.0689
  -6.500  -0.1564   0.02349   0.01632  -0.1215   0.8619   0.0698
  -6.250  -0.1286   0.02237   0.01494  -0.1213   0.8577   0.0710
  -6.000  -0.1047   0.02136   0.01378  -0.1206   0.8518   0.0722
  -5.750  -0.0814   0.02060   0.01306  -0.1198   0.8448   0.0741
  -5.500  -0.0524   0.01995   0.01235  -0.1198   0.8405   0.0768
  -5.250  -0.0265   0.01939   0.01167  -0.1192   0.8350   0.0795
  -5.000  -0.0037   0.01874   0.01098  -0.1182   0.8282   0.0820
  -4.750   0.0244   0.01815   0.01042  -0.1180   0.8238   0.0854
  -4.500   0.0533   0.01769   0.00985  -0.1179   0.8197   0.0903
  -4.250   0.0736   0.01730   0.00955  -0.1165   0.8122   0.0955
  -4.000   0.1011   0.01686   0.00906  -0.1162   0.8075   0.1039
  -3.750   0.1305   0.01636   0.00855  -0.1163   0.8040   0.1161
  -3.500   0.1501   0.01602   0.00833  -0.1148   0.7971   0.1322
  -3.250   0.1752   0.01562   0.00802  -0.1142   0.7918   0.1546
  -3.000   0.2050   0.01525   0.00766  -0.1143   0.7875   0.1790
  -2.750   0.2277   0.01509   0.00761  -0.1133   0.7808   0.2009
  -2.500   0.2539   0.01487   0.00742  -0.1127   0.7742   0.2277
  -2.250   0.2846   0.01456   0.00717  -0.1129   0.7694   0.2614
  -2.000   0.3061   0.01454   0.00727  -0.1116   0.7621   0.2927
  -1.750   0.3329   0.01443   0.00720  -0.1112   0.7560   0.3257
  -1.500   0.3642   0.01432   0.00705  -0.1114   0.7511   0.3597
  -1.250   0.3845   0.01435   0.00718  -0.1098   0.7429   0.3842
  -1.000   0.4131   0.01423   0.00704  -0.1096   0.7367   0.4088
  -0.750   0.4403   0.01419   0.00699  -0.1092   0.7311   0.4306
  -0.500   0.4636   0.01419   0.00703  -0.1081   0.7243   0.4505
  -0.250   0.4918   0.01407   0.00693  -0.1079   0.7190   0.4721
   0.000   0.5190   0.01399   0.00690  -0.1076   0.7138   0.4954
   0.250   0.5411   0.01396   0.00698  -0.1063   0.7070   0.5205
   0.500   0.5683   0.01378   0.00688  -0.1059   0.7012   0.5517
   0.750   0.5934   0.01358   0.00685  -0.1051   0.6954   0.5977
   1.000   0.6122   0.01305   0.00699  -0.1029   0.6882   0.7464
   1.250   0.7345   0.01266   0.00672  -0.1218   0.6813   1.0000
   1.500   0.7550   0.01280   0.00681  -0.1202   0.6735   1.0000
   1.750   0.7796   0.01284   0.00675  -0.1194   0.6659   1.0000
   2.000   0.8036   0.01293   0.00675  -0.1184   0.6587   1.0000
   2.250   0.8255   0.01301   0.00679  -0.1171   0.6502   1.0000
   2.500   0.8513   0.01305   0.00672  -0.1164   0.6426   1.0000
   2.750   0.8713   0.01312   0.00678  -0.1146   0.6325   1.0000
   3.000   0.8953   0.01317   0.00674  -0.1136   0.6237   1.0000
   3.250   0.9160   0.01322   0.00676  -0.1120   0.6130   1.0000
   3.500   0.9368   0.01329   0.00678  -0.1104   0.6017   1.0000
   3.750   0.9593   0.01332   0.00672  -0.1091   0.5900   1.0000
   4.000   0.9780   0.01339   0.00675  -0.1071   0.5759   1.0000
   4.250   0.9959   0.01348   0.00679  -0.1049   0.5599   1.0000
   4.500   1.0133   0.01360   0.00683  -0.1027   0.5418   1.0000
   4.750   1.0290   0.01377   0.00690  -0.1002   0.5212   1.0000
   5.000   1.0426   0.01400   0.00704  -0.0973   0.4977   1.0000
   5.250   1.0554   0.01433   0.00719  -0.0944   0.4745   1.0000
   5.500   1.0674   0.01474   0.00743  -0.0914   0.4527   1.0000
   5.750   1.0796   0.01518   0.00772  -0.0885   0.4334   1.0000
   6.000   1.0910   0.01565   0.00805  -0.0855   0.4172   1.0000
   6.250   1.1032   0.01615   0.00839  -0.0827   0.4036   1.0000
   6.500   1.1166   0.01660   0.00879  -0.0802   0.3913   1.0000
   6.750   1.1318   0.01709   0.00920  -0.0780   0.3809   1.0000
   7.000   1.1480   0.01761   0.00962  -0.0761   0.3717   1.0000
   7.250   1.1646   0.01808   0.01008  -0.0743   0.3631   1.0000
   7.500   1.1819   0.01862   0.01052  -0.0727   0.3549   1.0000
   7.750   1.1988   0.01912   0.01102  -0.0711   0.3472   1.0000
   8.000   1.2154   0.01963   0.01149  -0.0694   0.3397   1.0000
   8.250   1.2338   0.02019   0.01201  -0.0681   0.3326   1.0000
   8.500   1.2489   0.02070   0.01256  -0.0662   0.3256   1.0000
   8.750   1.2700   0.02131   0.01304  -0.0654   0.3189   1.0000
   9.000   1.2834   0.02184   0.01367  -0.0634   0.3125   1.0000
   9.250   1.2986   0.02241   0.01425  -0.0617   0.3061   1.0000
   9.500   1.3185   0.02304   0.01481  -0.0608   0.2998   1.0000
   9.750   1.3297   0.02365   0.01552  -0.0586   0.2934   1.0000
  10.000   1.3446   0.02428   0.01613  -0.0570   0.2871   1.0000
  10.250   1.3592   0.02498   0.01685  -0.0554   0.2808   1.0000
  10.500   1.3696   0.02568   0.01762  -0.0533   0.2742   1.0000
  10.750   1.3862   0.02639   0.01823  -0.0521   0.2679   1.0000
  11.000   1.3941   0.02722   0.01921  -0.0499   0.2617   1.0000
  11.250   1.4045   0.02803   0.02005  -0.0481   0.2556   1.0000
  11.500   1.4197   0.02884   0.02080  -0.0468   0.2497   1.0000
  11.750   1.4267   0.02982   0.02191  -0.0448   0.2435   1.0000
  12.000   1.4376   0.03072   0.02281  -0.0432   0.2379   1.0000
  12.250   1.4499   0.03170   0.02381  -0.0418   0.2323   1.0000
  12.500   1.4578   0.03279   0.02500  -0.0401   0.2266   1.0000
  12.750   1.4692   0.03377   0.02595  -0.0388   0.2216   1.0000
  13.000   1.4799   0.03489   0.02711  -0.0375   0.2165   1.0000
  13.250   1.4869   0.03614   0.02847  -0.0360   0.2114   1.0000
  13.500   1.4965   0.03726   0.02959  -0.0347   0.2069   1.0000
  13.750   1.5080   0.03841   0.03073  -0.0337   0.2023   1.0000
  14.000   1.5126   0.03990   0.03236  -0.0323   0.1979   1.0000
  14.250   1.5192   0.04128   0.03378  -0.0311   0.1935   1.0000
  14.500   1.5355   0.04217   0.03455  -0.0303   0.1892   1.0000
  14.750   1.5365   0.04403   0.03662  -0.0290   0.1858   1.0000
  15.000   1.5414   0.04568   0.03838  -0.0280   0.1821   1.0000
  15.250   1.5484   0.04719   0.03992  -0.0271   0.1785   1.0000
  15.500   1.5648   0.04807   0.04070  -0.0265   0.1748   1.0000
  15.750   1.5643   0.05027   0.04312  -0.0255   0.1721   1.0000
  16.000   1.5674   0.05225   0.04524  -0.0247   0.1691   1.0000
  16.250   1.5724   0.05408   0.04714  -0.0241   0.1661   1.0000
  16.500   1.5793   0.05569   0.04875  -0.0235   0.1629   1.0000
  16.750   1.5890   0.05719   0.05027  -0.0229   0.1599   1.0000
  17.000   1.5864   0.05987   0.05316  -0.0224   0.1576   1.0000
  17.250   1.5859   0.06240   0.05583  -0.0221   0.1548   1.0000
  17.500   1.5875   0.06472   0.05824  -0.0218   0.1519   1.0000
  17.750   1.5936   0.06653   0.06003  -0.0216   0.1488   1.0000
  18.000   1.5957   0.06891   0.06248  -0.0214   0.1460   1.0000
  18.250   1.5861   0.07272   0.06652  -0.0216   0.1434   1.0000
  18.500   1.5812   0.07606   0.07001  -0.0220   0.1404   1.0000
  18.750   1.5794   0.07904   0.07304  -0.0223   0.1374   1.0000
  19.000   1.5845   0.08107   0.07502  -0.0224   0.1337   1.0000
  19.250   1.5692   0.08609   0.08029  -0.0236   0.1312   1.0000
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