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GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL (goe188-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.07 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe188-il-1000000.txt
Download as CSV file: xf-goe188-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 188 (SCHTTE-LANZ 3U10) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2959   0.08422   0.08279  -0.0203   1.0000   0.0058
  -8.250  -0.2944   0.08062   0.07920  -0.0212   1.0000   0.0059
  -8.000  -0.3966   0.09046   0.08896  -0.0156   1.0000   0.0056
  -7.750  -0.3932   0.08713   0.08565  -0.0171   1.0000   0.0056
  -7.500  -0.3910   0.08383   0.08238  -0.0189   1.0000   0.0057
  -7.250  -0.3841   0.08007   0.07863  -0.0225   1.0000   0.0057
  -7.000  -0.3759   0.07627   0.07482  -0.0259   1.0000   0.0057
  -6.750  -0.3628   0.07217   0.07072  -0.0302   0.9972   0.0058
  -6.500  -0.3310   0.06666   0.06514  -0.0393   0.9608   0.0059
  -6.250  -0.3107   0.06249   0.06066  -0.0437   0.8760   0.0060
  -6.000  -0.2941   0.05878   0.05675  -0.0465   0.8434   0.0061
  -5.750  -0.2748   0.05501   0.05282  -0.0492   0.8240   0.0062
  -5.500  -0.2540   0.05131   0.04896  -0.0516   0.8090   0.0064
  -5.250  -0.2320   0.04770   0.04520  -0.0536   0.7961   0.0066
  -5.000  -0.2088   0.04422   0.04155  -0.0552   0.7840   0.0068
  -4.750  -0.1846   0.04087   0.03802  -0.0564   0.7726   0.0072
  -4.500  -0.1574   0.03764   0.03459  -0.0570   0.7617   0.0078
  -4.250  -0.1272   0.03474   0.03144  -0.0570   0.7520   0.0081
  -4.000  -0.1007   0.03196   0.02844  -0.0570   0.7426   0.0081
  -3.750  -0.0743   0.02916   0.02539  -0.0568   0.7332   0.0082
  -3.500  -0.0511   0.02451   0.02042  -0.0570   0.7249   0.0086
  -3.250  -0.0263   0.02293   0.01868  -0.0573   0.7155   0.0090
  -3.000   0.0004   0.02137   0.01695  -0.0573   0.7057   0.0097
  -2.750   0.0294   0.01998   0.01533  -0.0568   0.6968   0.0111
  -2.500   0.0595   0.01959   0.01469  -0.0561   0.6883   0.0118
  -2.250   0.0878   0.01831   0.01316  -0.0558   0.6799   0.0118
  -2.000   0.1151   0.01516   0.00968  -0.0557   0.6725   0.0124
  -1.750   0.1427   0.01396   0.00839  -0.0558   0.6640   0.0129
  -1.500   0.1709   0.01308   0.00738  -0.0558   0.6559   0.0135
  -1.250   0.1993   0.01234   0.00651  -0.0557   0.6476   0.0146
  -1.000   0.2282   0.01193   0.00599  -0.0556   0.6399   0.0163
  -0.750   0.2572   0.01204   0.00596  -0.0554   0.6319   0.0172
  -0.250   0.3135   0.00956   0.00332  -0.0550   0.6159   0.0179
   0.000   0.3415   0.00899   0.00272  -0.0550   0.6064   0.0181
   0.250   0.3701   0.00889   0.00259  -0.0550   0.5967   0.0171
   0.500   0.3983   0.00832   0.00195  -0.0550   0.5868   0.0166
   0.750   0.4267   0.00810   0.00164  -0.0551   0.5742   0.0178
   1.000   0.4552   0.00794   0.00139  -0.0551   0.5583   0.0203
   1.250   0.4834   0.00792   0.00128  -0.0552   0.5376   0.0238
   1.500   0.5114   0.00797   0.00122  -0.0553   0.5098   0.0358
   1.750   0.5347   0.00579   0.00133  -0.0550   0.4796   1.0000
   2.000   0.5619   0.00601   0.00137  -0.0550   0.4512   1.0000
   2.250   0.5892   0.00620   0.00144  -0.0550   0.4291   1.0000
   2.500   0.6168   0.00638   0.00152  -0.0550   0.4117   1.0000
   2.750   0.6444   0.00654   0.00159  -0.0551   0.3980   1.0000
   3.000   0.6722   0.00669   0.00168  -0.0552   0.3870   1.0000
   3.250   0.6999   0.00684   0.00177  -0.0553   0.3772   1.0000
   3.500   0.7277   0.00697   0.00187  -0.0554   0.3682   1.0000
   3.750   0.7555   0.00710   0.00197  -0.0555   0.3600   1.0000
   4.000   0.7832   0.00726   0.00208  -0.0556   0.3518   1.0000
   4.250   0.8111   0.00737   0.00219  -0.0557   0.3451   1.0000
   4.500   0.8386   0.00754   0.00233  -0.0558   0.3363   1.0000
   4.750   0.8662   0.00768   0.00245  -0.0559   0.3266   1.0000
   5.000   0.8938   0.00783   0.00258  -0.0560   0.3172   1.0000
   5.250   0.9211   0.00802   0.00273  -0.0561   0.3085   1.0000
   5.500   0.9487   0.00815   0.00288  -0.0562   0.3002   1.0000
   5.750   0.9760   0.00832   0.00304  -0.0563   0.2915   1.0000
   6.000   1.0032   0.00850   0.00321  -0.0564   0.2824   1.0000
   6.250   1.0304   0.00867   0.00338  -0.0565   0.2723   1.0000
   6.500   1.0573   0.00888   0.00358  -0.0565   0.2590   1.0000
   6.750   1.0837   0.00914   0.00380  -0.0565   0.2430   1.0000
   7.000   1.1092   0.00952   0.00407  -0.0564   0.2163   1.0000
   7.250   1.1331   0.01008   0.00446  -0.0561   0.1820   1.0000
   7.500   1.1569   0.01066   0.00490  -0.0558   0.1531   1.0000
   7.750   1.1794   0.01139   0.00541  -0.0553   0.1135   1.0000
   8.000   1.1993   0.01241   0.00616  -0.0545   0.0681   1.0000
   8.250   1.2228   0.01296   0.00667  -0.0541   0.0549   1.0000
   8.500   1.2465   0.01345   0.00715  -0.0537   0.0463   1.0000
   8.750   1.2699   0.01396   0.00763  -0.0533   0.0386   1.0000
   9.000   1.2934   0.01443   0.00810  -0.0529   0.0310   1.0000
   9.250   1.3123   0.01541   0.00893  -0.0519   0.0126   1.0000
   9.500   1.3325   0.01624   0.00980  -0.0510   0.0090   1.0000
   9.750   1.3538   0.01685   0.01051  -0.0502   0.0079   1.0000
  10.000   1.3731   0.01766   0.01139  -0.0492   0.0068   1.0000
  10.250   1.3882   0.01884   0.01272  -0.0476   0.0060   1.0000
  10.500   1.4073   0.01954   0.01349  -0.0466   0.0057   1.0000
  10.750   1.4243   0.02038   0.01443  -0.0453   0.0053   1.0000
  11.000   1.4394   0.02131   0.01545  -0.0438   0.0050   1.0000
  11.250   1.4527   0.02229   0.01652  -0.0421   0.0047   1.0000
  11.500   1.4628   0.02336   0.01770  -0.0400   0.0044   1.0000
  11.750   1.4655   0.02462   0.01907  -0.0367   0.0042   1.0000
  12.000   1.4628   0.02642   0.02100  -0.0334   0.0040   1.0000
  12.250   1.4491   0.02943   0.02420  -0.0302   0.0038   1.0000
  12.500   1.4451   0.03211   0.02703  -0.0287   0.0037   1.0000
  12.750   1.4550   0.03363   0.02864  -0.0283   0.0036   1.0000
  13.000   1.4585   0.03591   0.03103  -0.0279   0.0034   1.0000
  13.250   1.4595   0.03855   0.03378  -0.0277   0.0033   1.0000
  13.500   1.4574   0.04168   0.03704  -0.0277   0.0032   1.0000
  13.750   1.4539   0.04506   0.04055  -0.0278   0.0031   1.0000
  14.000   1.4483   0.04885   0.04446  -0.0283   0.0031   1.0000
  14.250   1.4420   0.05279   0.04853  -0.0288   0.0030   1.0000
  14.500   1.4342   0.05702   0.05289  -0.0296   0.0029   1.0000
  14.750   1.4254   0.06150   0.05749  -0.0307   0.0029   1.0000
  15.000   1.4151   0.06630   0.06242  -0.0319   0.0029   1.0000
  15.250   1.4047   0.07137   0.06761  -0.0334   0.0028   1.0000
  15.500   1.3944   0.07661   0.07297  -0.0351   0.0028   1.0000
  15.750   1.3838   0.08203   0.07852  -0.0370   0.0028   1.0000
  16.000   1.3722   0.08775   0.08435  -0.0391   0.0027   1.0000
  16.250   1.3598   0.09365   0.09038  -0.0413   0.0027   1.0000
  16.500   1.3479   0.09956   0.09640  -0.0436   0.0027   1.0000
  16.750   1.3363   0.10555   0.10250  -0.0461   0.0027   1.0000
  17.000   1.3237   0.11180   0.10887  -0.0487   0.0027   1.0000
  17.250   1.3118   0.11798   0.11516  -0.0513   0.0026   1.0000
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