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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 200,000
Max Cl/Cd: 75.29 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe330-il-200000-n5.txt
Download as CSV file: xf-goe330-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 330 (PFALZ 59) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1966   0.10339   0.09991  -0.0543   0.9832   0.0264
  -9.000  -0.1844   0.10004   0.09656  -0.0613   0.9765   0.0290
  -8.750  -0.1737   0.09637   0.09290  -0.0669   0.9686   0.0292
  -8.500  -0.0688   0.07505   0.07170  -0.0792   0.9399   0.0298
  -8.250  -0.0499   0.07209   0.06873  -0.0779   0.9362   0.0314
  -8.000  -0.0407   0.06917   0.06580  -0.0790   0.9298   0.0332
  -7.750  -0.1272   0.08028   0.07680  -0.0817   0.9385   0.0298
  -7.500  -0.1105   0.07816   0.07467  -0.0792   0.9356   0.0313
  -7.250  -0.0971   0.07552   0.07202  -0.0815   0.9276   0.0332
  -7.000  -0.0811   0.07210   0.06857  -0.0863   0.9198   0.0355
  -6.750  -0.0560   0.06705   0.06341  -0.0998   0.9085   0.0375
  -6.500  -0.0322   0.06235   0.05860  -0.1063   0.9025   0.0376
  -6.250  -0.0173   0.05777   0.05396  -0.1094   0.8938   0.0381
  -6.000  -0.0059   0.05614   0.05236  -0.1068   0.8882   0.0393
  -5.750   0.0114   0.05384   0.05001  -0.1077   0.8792   0.0408
  -5.500   0.0353   0.05047   0.04650  -0.1113   0.8719   0.0421
  -5.250   0.0587   0.04686   0.04275  -0.1147   0.8628   0.0426
  -5.000   0.0935   0.03935   0.03473  -0.1218   0.8561   0.0371
  -4.750   0.1151   0.03641   0.03162  -0.1228   0.8480   0.0365
  -4.500   0.1406   0.03320   0.02814  -0.1242   0.8418   0.0361
  -4.250   0.1647   0.03020   0.02483  -0.1248   0.8333   0.0362
  -4.000   0.1922   0.02724   0.02139  -0.1253   0.8264   0.0373
  -3.750   0.2160   0.02500   0.01885  -0.1252   0.8175   0.0372
  -3.500   0.2421   0.02294   0.01642  -0.1252   0.8102   0.0372
  -3.250   0.2671   0.02123   0.01437  -0.1248   0.8006   0.0373
  -3.000   0.2931   0.01980   0.01259  -0.1244   0.7916   0.0375
  -2.750   0.3190   0.01846   0.01098  -0.1242   0.7826   0.0385
  -2.500   0.3447   0.01768   0.01007  -0.1238   0.7732   0.0395
  -2.250   0.3717   0.01680   0.00896  -0.1235   0.7645   0.0398
  -2.000   0.3977   0.01602   0.00801  -0.1231   0.7539   0.0401
  -1.750   0.4241   0.01537   0.00721  -0.1226   0.7432   0.0406
  -1.500   0.4506   0.01480   0.00652  -0.1222   0.7318   0.0412
  -1.250   0.4770   0.01432   0.00592  -0.1218   0.7195   0.0419
  -1.000   0.5032   0.01390   0.00542  -0.1213   0.7065   0.0428
  -0.750   0.5294   0.01355   0.00499  -0.1208   0.6930   0.0438
  -0.500   0.5555   0.01332   0.00465  -0.1204   0.6792   0.0458
  -0.250   0.5815   0.01311   0.00435  -0.1199   0.6657   0.0477
   0.000   0.6074   0.01295   0.00414  -0.1194   0.6529   0.0495
   0.250   0.6333   0.01287   0.00397  -0.1190   0.6408   0.0517
   0.750   0.6850   0.01281   0.00377  -0.1181   0.6158   0.0608
   1.000   0.7107   0.01280   0.00370  -0.1176   0.6031   0.0724
   1.250   0.7363   0.01281   0.00365  -0.1172   0.5904   0.0875
   1.500   0.7614   0.01276   0.00369  -0.1167   0.5768   0.1278
   2.000   0.8214   0.01133   0.00396  -0.1180   0.5424   1.0000
   2.500   0.8679   0.01179   0.00411  -0.1161   0.5014   1.0000
   2.750   0.8906   0.01205   0.00421  -0.1152   0.4824   1.0000
   3.000   0.9134   0.01233   0.00435  -0.1142   0.4671   1.0000
   3.250   0.9364   0.01262   0.00452  -0.1134   0.4549   1.0000
   3.500   0.9595   0.01291   0.00471  -0.1125   0.4441   1.0000
   3.750   0.9829   0.01319   0.00492  -0.1118   0.4342   1.0000
   4.000   1.0059   0.01350   0.00515  -0.1110   0.4252   1.0000
   4.250   1.0294   0.01379   0.00539  -0.1103   0.4164   1.0000
   4.500   1.0527   0.01410   0.00564  -0.1095   0.4089   1.0000
   4.750   1.0765   0.01438   0.00591  -0.1089   0.4017   1.0000
   5.000   1.0995   0.01471   0.00618  -0.1081   0.3954   1.0000
   5.250   1.1235   0.01496   0.00646  -0.1076   0.3885   1.0000
   5.500   1.1465   0.01528   0.00677  -0.1068   0.3820   1.0000
   5.750   1.1699   0.01556   0.00708  -0.1062   0.3762   1.0000
   6.000   1.1933   0.01585   0.00740  -0.1055   0.3705   1.0000
   6.250   1.2160   0.01618   0.00773  -0.1047   0.3652   1.0000
   6.500   1.2392   0.01647   0.00809  -0.1041   0.3599   1.0000
   6.750   1.2620   0.01677   0.00845  -0.1033   0.3542   1.0000
   7.000   1.2836   0.01713   0.00883  -0.1024   0.3488   1.0000
   7.250   1.3052   0.01742   0.00921  -0.1015   0.3402   1.0000
   7.500   1.3242   0.01779   0.00960  -0.1001   0.3291   1.0000
   7.750   1.3419   0.01819   0.01000  -0.0986   0.3164   1.0000
   8.000   1.3587   0.01859   0.01042  -0.0969   0.3019   1.0000
   8.250   1.3740   0.01905   0.01088  -0.0950   0.2859   1.0000
   8.500   1.3884   0.01958   0.01142  -0.0930   0.2661   1.0000
   8.750   1.3988   0.02032   0.01207  -0.0905   0.2392   1.0000
   9.000   1.4057   0.02135   0.01293  -0.0876   0.2071   1.0000
   9.250   1.4099   0.02264   0.01403  -0.0846   0.1792   1.0000
   9.500   1.4147   0.02398   0.01526  -0.0819   0.1583   1.0000
  10.000   1.3959   0.02894   0.01950  -0.0740   0.0430   1.0000
  10.250   1.3929   0.03115   0.02167  -0.0711   0.0289   1.0000
  10.500   1.3969   0.03289   0.02349  -0.0691   0.0247   1.0000
  10.750   1.4030   0.03451   0.02524  -0.0674   0.0224   1.0000
  11.000   1.4070   0.03635   0.02721  -0.0656   0.0209   1.0000
  11.250   1.4086   0.03848   0.02948  -0.0639   0.0197   1.0000
  11.500   1.4087   0.04082   0.03197  -0.0623   0.0188   1.0000
  11.750   1.4110   0.04303   0.03434  -0.0611   0.0180   1.0000
  12.000   1.4115   0.04549   0.03695  -0.0599   0.0172   1.0000
  12.250   1.4101   0.04825   0.03988  -0.0589   0.0165   1.0000
  12.500   1.4073   0.05129   0.04307  -0.0582   0.0159   1.0000
  12.750   1.4025   0.05473   0.04666  -0.0577   0.0154   1.0000
  13.000   1.3960   0.05853   0.05060  -0.0575   0.0150   1.0000
  13.250   1.3877   0.06272   0.05494  -0.0575   0.0147   1.0000
  13.500   1.3776   0.06728   0.05964  -0.0577   0.0145   1.0000
  13.750   1.3664   0.07212   0.06461  -0.0582   0.0142   1.0000
  14.000   1.3546   0.07717   0.06978  -0.0588   0.0140   1.0000
  14.250   1.3436   0.08215   0.07487  -0.0596   0.0138   1.0000
  14.500   1.3381   0.08641   0.07924  -0.0602   0.0137   1.0000
  14.750   1.3334   0.09057   0.08352  -0.0608   0.0135   1.0000
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