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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 500,000
Max Cl/Cd: 68.84 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe235-il-500000-n5.txt
Download as CSV file: xf-goe235-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 235 (SCHTTE-LANZ) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4807   0.10918   0.10678   0.0073   1.0000   0.0210
  -9.000  -0.4759   0.10558   0.10318   0.0050   1.0000   0.0211
  -8.750  -0.4724   0.10181   0.09943   0.0021   1.0000   0.0211
  -8.500  -0.4660   0.09830   0.09593   0.0008   1.0000   0.0212
  -8.250  -0.4566   0.09560   0.09325   0.0006   1.0000   0.0214
  -8.000  -0.4484   0.09289   0.09056  -0.0005   1.0000   0.0216
  -7.750  -0.4407   0.09006   0.08775  -0.0021   1.0000   0.0219
  -7.500  -0.4329   0.08712   0.08483  -0.0042   1.0000   0.0221
  -7.250  -0.4216   0.08388   0.08160  -0.0075   1.0000   0.0226
  -7.000  -0.4083   0.08042   0.07814  -0.0114   1.0000   0.0232
  -6.750  -0.3892   0.07569   0.07339  -0.0191   0.9943   0.0245
  -6.500  -0.3605   0.07004   0.06767  -0.0291   0.9693   0.0247
  -6.250  -0.3330   0.06449   0.06201  -0.0374   0.9494   0.0248
  -6.000  -0.3108   0.06018   0.05760  -0.0416   0.9295   0.0248
  -5.750  -0.2889   0.05609   0.05338  -0.0449   0.9056   0.0248
  -5.500  -0.2702   0.05243   0.04957  -0.0468   0.8816   0.0249
  -5.250  -0.2534   0.05034   0.04738  -0.0469   0.8609   0.0251
  -5.000  -0.2329   0.04814   0.04506  -0.0478   0.8427   0.0253
  -4.750  -0.2095   0.04570   0.04249  -0.0494   0.8273   0.0256
  -4.500  -0.1843   0.04317   0.03980  -0.0511   0.8142   0.0261
  -4.250  -0.1577   0.04081   0.03730  -0.0528   0.8028   0.0274
  -4.000  -0.1192   0.03576   0.03185  -0.0563   0.7934   0.0288
  -3.750  -0.0905   0.02914   0.02479  -0.0586   0.7843   0.0249
  -3.500  -0.0627   0.02652   0.02192  -0.0592   0.7717   0.0249
  -3.250  -0.0362   0.02473   0.01995  -0.0598   0.7565   0.0251
  -3.000  -0.0096   0.02379   0.01892  -0.0601   0.7409   0.0254
  -2.750   0.0175   0.02275   0.01774  -0.0603   0.7238   0.0259
  -2.500   0.0465   0.02054   0.01519  -0.0605   0.7038   0.0259
  -2.250   0.0753   0.01856   0.01285  -0.0606   0.6802   0.0259
  -2.000   0.1037   0.01723   0.01121  -0.0606   0.6600   0.0261
  -1.750   0.1322   0.01607   0.00979  -0.0606   0.6446   0.0264
  -1.500   0.1607   0.01505   0.00852  -0.0606   0.6305   0.0267
  -1.250   0.1893   0.01410   0.00735  -0.0605   0.6179   0.0271
  -1.000   0.2178   0.01328   0.00632  -0.0604   0.6049   0.0277
  -0.750   0.2463   0.01252   0.00534  -0.0603   0.5923   0.0285
  -0.500   0.2748   0.01189   0.00457  -0.0602   0.5789   0.0288
  -0.250   0.3028   0.01142   0.00396  -0.0601   0.5525   0.0292
   0.000   0.3297   0.01139   0.00356  -0.0600   0.4588   0.0296
   0.250   0.3566   0.01157   0.00342  -0.0599   0.3867   0.0301
   0.500   0.3839   0.01166   0.00327  -0.0599   0.3280   0.0307
   0.750   0.4103   0.01202   0.00321  -0.0599   0.2327   0.0313
   1.000   0.4380   0.01200   0.00309  -0.0598   0.2112   0.0320
   1.250   0.4658   0.01199   0.00301  -0.0598   0.1988   0.0332
   1.500   0.4937   0.01194   0.00291  -0.0597   0.1893   0.0341
   1.750   0.5217   0.01187   0.00284  -0.0596   0.1826   0.0350
   2.000   0.5496   0.01186   0.00283  -0.0596   0.1766   0.0360
   2.250   0.5774   0.01191   0.00283  -0.0595   0.1677   0.0373
   2.500   0.6054   0.01191   0.00284  -0.0594   0.1617   0.0387
   2.750   0.6331   0.01198   0.00287  -0.0594   0.1528   0.0405
   3.000   0.6608   0.01206   0.00294  -0.0593   0.1417   0.0434
   3.250   0.6855   0.01291   0.00333  -0.0590   0.0418   0.0458
   3.500   0.7127   0.01308   0.00348  -0.0589   0.0370   0.0499
   3.750   0.7401   0.01324   0.00365  -0.0587   0.0350   0.0556
   4.250   0.7902   0.01176   0.00419  -0.0579   0.0332   1.0000
   4.500   0.8172   0.01203   0.00444  -0.0577   0.0324   1.0000
   4.750   0.8441   0.01233   0.00472  -0.0575   0.0317   1.0000
   5.000   0.8707   0.01266   0.00505  -0.0572   0.0311   1.0000
   5.250   0.8970   0.01303   0.00542  -0.0570   0.0305   1.0000
   5.500   0.9230   0.01347   0.00586  -0.0566   0.0298   1.0000
   5.750   0.9487   0.01392   0.00632  -0.0563   0.0292   1.0000
   6.000   0.9748   0.01429   0.00670  -0.0560   0.0288   1.0000
   6.250   1.0004   0.01470   0.00713  -0.0557   0.0284   1.0000
   6.500   1.0258   0.01515   0.00761  -0.0553   0.0281   1.0000
   6.750   1.0509   0.01563   0.00811  -0.0549   0.0277   1.0000
   7.000   1.0756   0.01613   0.00864  -0.0545   0.0273   1.0000
   7.250   1.1000   0.01667   0.00921  -0.0540   0.0270   1.0000
   7.500   1.1240   0.01724   0.00981  -0.0535   0.0266   1.0000
   7.750   1.1477   0.01783   0.01043  -0.0529   0.0262   1.0000
   8.000   1.1710   0.01844   0.01106  -0.0524   0.0258   1.0000
   8.250   1.1937   0.01911   0.01176  -0.0517   0.0253   1.0000
   8.500   1.2153   0.01989   0.01257  -0.0510   0.0249   1.0000
   8.750   1.2354   0.02087   0.01358  -0.0501   0.0246   1.0000
   9.000   1.2550   0.02192   0.01466  -0.0491   0.0242   1.0000
   9.250   1.2766   0.02260   0.01541  -0.0484   0.0240   1.0000
   9.500   1.2978   0.02330   0.01618  -0.0476   0.0238   1.0000
   9.750   1.3186   0.02401   0.01696  -0.0467   0.0234   1.0000
  10.000   1.3386   0.02478   0.01781  -0.0458   0.0230   1.0000
  10.250   1.3577   0.02563   0.01874  -0.0448   0.0226   1.0000
  10.500   1.3759   0.02655   0.01973  -0.0437   0.0223   1.0000
  10.750   1.3933   0.02749   0.02075  -0.0426   0.0219   1.0000
  11.000   1.4099   0.02845   0.02179  -0.0414   0.0216   1.0000
  11.250   1.4257   0.02938   0.02279  -0.0401   0.0212   1.0000
  11.500   1.4404   0.03033   0.02380  -0.0388   0.0209   1.0000
  11.750   1.4525   0.03133   0.02485  -0.0371   0.0207   1.0000
  12.000   1.4614   0.03246   0.02604  -0.0351   0.0204   1.0000
  12.250   1.4688   0.03389   0.02753  -0.0331   0.0202   1.0000
  12.500   1.4750   0.03554   0.02927  -0.0313   0.0200   1.0000
  12.750   1.4815   0.03701   0.03088  -0.0297   0.0198   1.0000
  13.000   1.4868   0.03867   0.03270  -0.0283   0.0195   1.0000
  13.250   1.4910   0.04056   0.03474  -0.0272   0.0192   1.0000
  13.500   1.4943   0.04263   0.03697  -0.0264   0.0189   1.0000
  13.750   1.4966   0.04488   0.03937  -0.0257   0.0186   1.0000
  14.000   1.4978   0.04735   0.04198  -0.0254   0.0183   1.0000
  14.250   1.4981   0.05003   0.04479  -0.0252   0.0180   1.0000
  14.500   1.4972   0.05296   0.04786  -0.0254   0.0178   1.0000
  14.750   1.4953   0.05616   0.05118  -0.0259   0.0176   1.0000
  15.000   1.4924   0.05962   0.05477  -0.0267   0.0175   1.0000
  15.250   1.4883   0.06335   0.05863  -0.0278   0.0173   1.0000
  15.500   1.4829   0.06737   0.06277  -0.0291   0.0172   1.0000
  15.750   1.4765   0.07169   0.06721  -0.0307   0.0171   1.0000
  16.000   1.4688   0.07632   0.07196  -0.0326   0.0170   1.0000
  16.250   1.4607   0.08128   0.07704  -0.0349   0.0169   1.0000
  16.500   1.4518   0.08662   0.08251  -0.0375   0.0168   1.0000
  16.750   1.4424   0.09223   0.08822  -0.0404   0.0167   1.0000
  17.000   1.4318   0.09817   0.09428  -0.0434   0.0166   1.0000
  17.250   1.4208   0.10433   0.10056  -0.0467   0.0165   1.0000
  17.500   1.4086   0.11084   0.10717  -0.0502   0.0165   1.0000
  18.000   1.3740   0.12649   0.12313  -0.0591   0.0163   1.0000
  18.250   1.3501   0.13631   0.13315  -0.0650   0.0162   1.0000
  18.500   1.3202   0.14796   0.14501  -0.0722   0.0160   1.0000
  18.750   1.2765   0.16400   0.16132  -0.0827   0.0159   1.0000
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