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GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 235 (SCHTTE-LANZ) AIRFOIL (goe235-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.61 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe235-il-1000000-n5.txt
Download as CSV file: xf-goe235-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4954   0.10620   0.10449   0.0096   1.0000   0.0140
  -9.000  -0.4900   0.10269   0.10099   0.0078   1.0000   0.0142
  -8.750  -0.4945   0.09617   0.09447   0.0038   1.0000   0.0152
  -8.500  -0.4859   0.09371   0.09202   0.0025   1.0000   0.0153
  -8.250  -0.4772   0.09121   0.08953   0.0010   1.0000   0.0154
  -8.000  -0.4690   0.08856   0.08690  -0.0008   1.0000   0.0155
  -7.750  -0.4574   0.08538   0.08371  -0.0042   0.9599   0.0156
  -7.500  -0.4479   0.08227   0.08053  -0.0070   0.9260   0.0158
  -7.250  -0.4379   0.07906   0.07719  -0.0099   0.8800   0.0159
  -7.000  -0.4239   0.07548   0.07347  -0.0139   0.8527   0.0161
  -6.500  -0.3879   0.06750   0.06531  -0.0236   0.8244   0.0166
  -6.250  -0.3666   0.06314   0.06085  -0.0288   0.8144   0.0169
  -6.000  -0.3381   0.05381   0.05133  -0.0397   0.8069   0.0180
  -5.750  -0.3144   0.05076   0.04818  -0.0426   0.7975   0.0182
  -5.500  -0.2901   0.04822   0.04555  -0.0448   0.7874   0.0183
  -5.250  -0.2646   0.04547   0.04271  -0.0471   0.7773   0.0184
  -5.000  -0.2383   0.04263   0.03974  -0.0494   0.7662   0.0186
  -4.750  -0.2112   0.03965   0.03662  -0.0516   0.7520   0.0187
  -4.500  -0.1838   0.03701   0.03382  -0.0533   0.7332   0.0191
  -4.250  -0.1558   0.03405   0.03063  -0.0550   0.7021   0.0195
  -4.000  -0.1268   0.03053   0.02679  -0.0567   0.6702   0.0198
  -3.750  -0.0970   0.02646   0.02238  -0.0581   0.6537   0.0203
  -3.500  -0.0673   0.02206   0.01755  -0.0591   0.6428   0.0206
  -3.250  -0.0377   0.01623   0.01104  -0.0599   0.6351   0.0215
  -3.000  -0.0097   0.01541   0.01006  -0.0600   0.6251   0.0217
  -2.750   0.0184   0.01464   0.00913  -0.0601   0.6151   0.0219
  -2.500   0.0467   0.01384   0.00818  -0.0602   0.6050   0.0222
  -2.250   0.0751   0.01283   0.00699  -0.0602   0.5962   0.0226
  -2.000   0.1036   0.01152   0.00545  -0.0603   0.5882   0.0231
  -1.750   0.1319   0.01066   0.00441  -0.0603   0.5768   0.0235
  -1.500   0.1603   0.01013   0.00376  -0.0602   0.5624   0.0239
  -1.250   0.1885   0.00983   0.00333  -0.0602   0.5380   0.0243
  -1.000   0.2159   0.01002   0.00309  -0.0602   0.4323   0.0246
  -0.750   0.2437   0.01001   0.00283  -0.0602   0.3765   0.0249
  -0.500   0.2715   0.00993   0.00254  -0.0603   0.3267   0.0254
  -0.250   0.2988   0.01029   0.00251  -0.0604   0.2257   0.0257
   0.000   0.3270   0.01029   0.00244  -0.0604   0.2076   0.0261
   0.250   0.3552   0.01027   0.00236  -0.0603   0.1931   0.0266
   0.500   0.3834   0.01025   0.00228  -0.0603   0.1819   0.0270
   0.750   0.4117   0.01020   0.00221  -0.0603   0.1754   0.0275
   1.000   0.4400   0.01018   0.00215  -0.0603   0.1680   0.0280
   1.250   0.4683   0.01015   0.00210  -0.0602   0.1639   0.0286
   1.500   0.4965   0.01016   0.00208  -0.0602   0.1578   0.0291
   1.750   0.5247   0.01016   0.00206  -0.0602   0.1511   0.0302
   2.000   0.5528   0.01022   0.00209  -0.0601   0.1405   0.0312
   2.250   0.5790   0.01086   0.00236  -0.0600   0.0460   0.0321
   2.500   0.6067   0.01102   0.00247  -0.0599   0.0336   0.0331
   2.750   0.6346   0.01112   0.00256  -0.0599   0.0315   0.0341
   3.000   0.6624   0.01122   0.00268  -0.0598   0.0299   0.0360
   3.250   0.6902   0.01134   0.00281  -0.0597   0.0291   0.0383
   3.500   0.7179   0.01145   0.00295  -0.0596   0.0287   0.0417
   3.750   0.7455   0.01159   0.00310  -0.0594   0.0282   0.0454
   4.000   0.7731   0.01173   0.00327  -0.0593   0.0277   0.0507
   4.250   0.8005   0.01189   0.00345  -0.0592   0.0272   0.0583
   4.500   0.8238   0.01030   0.00383  -0.0587   0.0268   1.0000
   4.750   0.8510   0.01054   0.00405  -0.0586   0.0264   1.0000
   5.000   0.8781   0.01080   0.00429  -0.0584   0.0259   1.0000
   5.250   0.9050   0.01109   0.00456  -0.0582   0.0254   1.0000
   5.500   0.9316   0.01143   0.00490  -0.0580   0.0247   1.0000
   5.750   0.9579   0.01183   0.00531  -0.0577   0.0243   1.0000
   6.000   0.9846   0.01211   0.00559  -0.0575   0.0241   1.0000
   6.250   1.0111   0.01241   0.00590  -0.0573   0.0240   1.0000
   6.500   1.0374   0.01273   0.00623  -0.0570   0.0238   1.0000
   6.750   1.0635   0.01307   0.00658  -0.0567   0.0235   1.0000
   7.000   1.0894   0.01342   0.00695  -0.0565   0.0233   1.0000
   7.250   1.1151   0.01380   0.00736  -0.0561   0.0230   1.0000
   7.500   1.1406   0.01419   0.00776  -0.0558   0.0227   1.0000
   7.750   1.1660   0.01457   0.00816  -0.0555   0.0224   1.0000
   8.000   1.1911   0.01497   0.00858  -0.0551   0.0220   1.0000
   8.250   1.2159   0.01540   0.00904  -0.0547   0.0218   1.0000
   8.500   1.2405   0.01585   0.00951  -0.0543   0.0215   1.0000
   8.750   1.2647   0.01631   0.00999  -0.0539   0.0212   1.0000
   9.000   1.2887   0.01679   0.01051  -0.0534   0.0210   1.0000
   9.250   1.3122   0.01731   0.01104  -0.0529   0.0207   1.0000
   9.500   1.3348   0.01792   0.01168  -0.0522   0.0204   1.0000
   9.750   1.3550   0.01880   0.01262  -0.0514   0.0200   1.0000
  10.000   1.3779   0.01930   0.01316  -0.0508   0.0199   1.0000
  10.250   1.4002   0.01983   0.01374  -0.0501   0.0197   1.0000
  10.500   1.4221   0.02039   0.01435  -0.0494   0.0195   1.0000
  10.750   1.4437   0.02094   0.01495  -0.0487   0.0193   1.0000
  11.000   1.4650   0.02149   0.01556  -0.0479   0.0189   1.0000
  11.250   1.4855   0.02209   0.01622  -0.0471   0.0186   1.0000
  11.500   1.5050   0.02275   0.01693  -0.0462   0.0184   1.0000
  11.750   1.5240   0.02342   0.01766  -0.0452   0.0181   1.0000
  12.000   1.5428   0.02405   0.01834  -0.0442   0.0178   1.0000
  12.250   1.5616   0.02463   0.01896  -0.0432   0.0176   1.0000
  12.500   1.5800   0.02519   0.01957  -0.0422   0.0173   1.0000
  12.750   1.5969   0.02582   0.02024  -0.0410   0.0171   1.0000
  13.000   1.6104   0.02654   0.02101  -0.0393   0.0169   1.0000
  13.250   1.6205   0.02741   0.02194  -0.0373   0.0167   1.0000
  13.500   1.6279   0.02855   0.02314  -0.0352   0.0165   1.0000
  13.750   1.6331   0.02996   0.02464  -0.0333   0.0163   1.0000
  14.000   1.6421   0.03119   0.02596  -0.0320   0.0162   1.0000
  14.250   1.6503   0.03258   0.02745  -0.0309   0.0160   1.0000
  14.500   1.6577   0.03415   0.02911  -0.0300   0.0158   1.0000
  14.750   1.6636   0.03594   0.03099  -0.0293   0.0156   1.0000
  15.000   1.6687   0.03791   0.03307  -0.0288   0.0154   1.0000
  15.250   1.6724   0.04011   0.03536  -0.0284   0.0152   1.0000
  15.500   1.6755   0.04249   0.03784  -0.0282   0.0150   1.0000
  15.750   1.6777   0.04508   0.04053  -0.0283   0.0148   1.0000
  16.000   1.6788   0.04791   0.04346  -0.0287   0.0146   1.0000
  16.250   1.6788   0.05103   0.04667  -0.0293   0.0145   1.0000
  16.500   1.6777   0.05437   0.05011  -0.0301   0.0143   1.0000
  16.750   1.6750   0.05798   0.05381  -0.0310   0.0142   1.0000
  17.000   1.6708   0.06189   0.05782  -0.0322   0.0140   1.0000
  17.250   1.6638   0.06634   0.06237  -0.0337   0.0139   1.0000
  17.500   1.6540   0.07138   0.06751  -0.0356   0.0138   1.0000
  17.750   1.6416   0.07714   0.07339  -0.0381   0.0137   1.0000
  18.000   1.6253   0.08371   0.08009  -0.0410   0.0136   1.0000
  18.250   1.6070   0.09071   0.08721  -0.0441   0.0135   1.0000
  18.500   1.5858   0.09832   0.09495  -0.0476   0.0135   1.0000
  18.750   1.5646   0.10599   0.10273  -0.0511   0.0134   1.0000
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