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GOE 392 AIRFOIL (goe392-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 392 AIRFOIL (goe392-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.59 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe392-il-1000000-n5.txt
Download as CSV file: xf-goe392-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 392 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2901   0.12618   0.12454  -0.0435   0.9968   0.0023
 -10.750  -0.2669   0.11811   0.11646  -0.0496   0.9938   0.0023
 -10.500  -0.2557   0.11462   0.11298  -0.0524   0.9920   0.0024
 -10.250  -0.2449   0.11080   0.10916  -0.0552   0.9902   0.0024
  -9.750  -0.2249   0.10354   0.10190  -0.0604   0.9861   0.0026
  -8.250  -0.1569   0.08055   0.07892  -0.0798   0.9491   0.0032
  -7.750  -0.0813   0.06547   0.06367  -0.1068   0.9102   0.0021
  -7.500  -0.0672   0.06152   0.05945  -0.1128   0.8532   0.0024
  -7.250  -0.0629   0.05995   0.05774  -0.1134   0.8243   0.0030
  -6.750  -0.0530   0.05230   0.04994  -0.1202   0.7930   0.0030
  -6.500  -0.0437   0.04732   0.04488  -0.1248   0.7815   0.0028
  -6.250  -0.0313   0.04191   0.03935  -0.1292   0.7717   0.0028
  -6.000  -0.0170   0.03748   0.03474  -0.1316   0.7627   0.0031
  -5.750  -0.0007   0.03274   0.02976  -0.1329   0.7542   0.0036
  -5.500   0.0152   0.02899   0.02576  -0.1333   0.7464   0.0034
  -5.250   0.0329   0.02542   0.02188  -0.1331   0.7385   0.0032
  -5.000   0.0519   0.02186   0.01796  -0.1324   0.7315   0.0030
  -4.750   0.0715   0.01799   0.01363  -0.1310   0.7237   0.0028
  -4.500   0.0887   0.01215   0.00699  -0.1282   0.7173   0.0026
  -4.250   0.1124   0.01092   0.00550  -0.1274   0.7094   0.0027
  -4.000   0.1367   0.01009   0.00447  -0.1267   0.7020   0.0030
  -3.750   0.1613   0.00951   0.00372  -0.1261   0.6934   0.0034
  -3.500   0.1867   0.00908   0.00315  -0.1257   0.6849   0.0038
  -3.250   0.2117   0.00867   0.00260  -0.1251   0.6751   0.0042
  -3.000   0.2372   0.00856   0.00242  -0.1248   0.6622   0.0053
  -2.750   0.2624   0.00836   0.00209  -0.1243   0.6469   0.0061
  -2.500   0.2877   0.00814   0.00172  -0.1238   0.6322   0.0079
  -2.250   0.3136   0.00805   0.00157  -0.1235   0.6203   0.0108
  -2.000   0.3397   0.00797   0.00145  -0.1232   0.6090   0.0189
  -1.750   0.3660   0.00794   0.00134  -0.1230   0.5980   0.0231
  -1.500   0.3922   0.00790   0.00124  -0.1228   0.5880   0.0291
  -1.250   0.4183   0.00789   0.00116  -0.1226   0.5780   0.0356
  -1.000   0.4445   0.00785   0.00109  -0.1224   0.5677   0.0484
  -0.750   0.4687   0.00743   0.00102  -0.1220   0.5591   0.1983
  -0.250   0.5197   0.00720   0.00105  -0.1215   0.5428   0.3317
   0.000   0.5460   0.00724   0.00107  -0.1213   0.5355   0.3524
   0.250   0.5724   0.00724   0.00110  -0.1212   0.5281   0.3768
   0.500   0.5985   0.00728   0.00113  -0.1210   0.5205   0.3917
   0.750   0.6251   0.00732   0.00116  -0.1208   0.5131   0.4014
   1.000   0.6510   0.00735   0.00121  -0.1206   0.5063   0.4213
   1.250   0.6772   0.00733   0.00126  -0.1205   0.5000   0.4467
   1.500   0.7029   0.00733   0.00132  -0.1202   0.4936   0.4788
   1.750   0.7258   0.00702   0.00145  -0.1195   0.4879   0.6556
   2.000   0.7497   0.00693   0.00155  -0.1189   0.4812   0.7300
   2.250   0.7688   0.00660   0.00166  -0.1170   0.4753   0.8955
   2.500   0.8224   0.00682   0.00185  -0.1233   0.4418   1.0000
   2.750   0.8436   0.00718   0.00202  -0.1222   0.4007   1.0000
   3.000   0.8621   0.00775   0.00228  -0.1206   0.3430   1.0000
   3.250   0.8742   0.00876   0.00276  -0.1178   0.2429   1.0000
   3.500   0.8738   0.01072   0.00384  -0.1128   0.0157   1.0000
   3.750   0.8976   0.01095   0.00408  -0.1122   0.0105   1.0000
   4.000   0.9210   0.01120   0.00436  -0.1115   0.0075   1.0000
   4.250   0.9439   0.01147   0.00466  -0.1107   0.0061   1.0000
   4.500   0.9651   0.01187   0.00512  -0.1095   0.0049   1.0000
   4.750   0.9879   0.01213   0.00538  -0.1087   0.0038   1.0000
   5.000   1.0091   0.01250   0.00578  -0.1076   0.0034   1.0000
   5.250   1.0273   0.01307   0.00642  -0.1059   0.0029   1.0000
   5.500   1.0449   0.01365   0.00709  -0.1040   0.0028   1.0000
   5.750   1.0599   0.01435   0.00790  -0.1016   0.0025   1.0000
   6.000   1.0705   0.01520   0.00886  -0.0984   0.0024   1.0000
   6.250   1.0773   0.01606   0.00981  -0.0945   0.0023   1.0000
   6.500   1.0824   0.01701   0.01084  -0.0904   0.0022   1.0000
   6.750   1.1079   0.01697   0.01078  -0.0905   0.0018   1.0000
   7.000   1.1112   0.01807   0.01196  -0.0863   0.0016   1.0000
   7.250   1.1133   0.01936   0.01336  -0.0821   0.0016   1.0000
   7.500   1.1181   0.02075   0.01484  -0.0784   0.0015   1.0000
   7.750   1.1307   0.02312   0.01728  -0.0756   0.0013   1.0000
   8.000   1.1961   0.02710   0.02135  -0.0815   0.0011   1.0000
   8.250   1.2414   0.03086   0.02532  -0.0840   0.0011   1.0000
   8.500   1.2674   0.03411   0.02880  -0.0832   0.0011   1.0000
   8.750   1.2856   0.03699   0.03190  -0.0814   0.0012   1.0000
   9.000   1.2985   0.03975   0.03486  -0.0791   0.0013   1.0000
   9.250   1.3065   0.04261   0.03794  -0.0762   0.0014   1.0000
   9.500   1.3092   0.04543   0.04096  -0.0730   0.0015   1.0000
   9.750   1.2999   0.04943   0.04518  -0.0689   0.0016   1.0000
  10.000   1.2976   0.05233   0.04826  -0.0652   0.0016   1.0000
  10.250   1.2905   0.05471   0.05081  -0.0608   0.0016   1.0000
  10.500   1.2797   0.05715   0.05341  -0.0561   0.0016   1.0000
  10.750   1.2674   0.05966   0.05608  -0.0518   0.0016   1.0000
  11.000   1.2531   0.06246   0.05903  -0.0480   0.0016   1.0000
  11.250   1.2383   0.06536   0.06208  -0.0449   0.0016   1.0000
  11.500   1.2223   0.06857   0.06544  -0.0423   0.0016   1.0000
  11.750   1.2065   0.07194   0.06895  -0.0405   0.0016   1.0000
  12.000   1.1897   0.07569   0.07284  -0.0393   0.0016   1.0000
  12.250   1.1709   0.08004   0.07733  -0.0387   0.0016   1.0000
  12.500   1.1532   0.08448   0.08190  -0.0388   0.0016   1.0000
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