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GOE 457 AIRFOIL (goe457-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 457 AIRFOIL (goe457-il)
Reynolds number: 1,000,000
Max Cl/Cd: 117 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe457-il-1000000.txt
Download as CSV file: xf-goe457-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 457 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3799   0.10650   0.10484  -0.0220   1.0000   0.0127
  -9.500  -0.3786   0.10330   0.10166  -0.0225   1.0000   0.0127
  -9.250  -0.3834   0.09888   0.09726  -0.0228   1.0000   0.0129
  -9.000  -0.3822   0.09623   0.09463  -0.0225   1.0000   0.0130
  -8.750  -0.3779   0.09456   0.09298  -0.0215   1.0000   0.0132
  -8.500  -0.3774   0.09268   0.09112  -0.0205   1.0000   0.0134
  -8.250  -0.3803   0.09088   0.08935  -0.0192   1.0000   0.0136
  -8.000  -0.3756   0.08794   0.08642  -0.0207   0.9993   0.0138
  -7.750  -0.3604   0.08422   0.08271  -0.0252   0.9974   0.0143
  -7.500  -0.3439   0.07998   0.07847  -0.0311   0.9946   0.0150
  -6.750  -0.2877   0.01866   0.01538  -0.0935   0.9735   0.0159
  -6.500  -0.2571   0.01602   0.01231  -0.0952   0.9722   0.0170
  -6.250  -0.2213   0.01630   0.01267  -0.0969   0.9714   0.0175
  -6.000  -0.1960   0.01630   0.01266  -0.0963   0.9665   0.0180
  -5.750  -0.1647   0.01573   0.01201  -0.0971   0.9637   0.0188
  -5.500  -0.1332   0.01467   0.01074  -0.0980   0.9612   0.0200
  -5.250  -0.0996   0.01419   0.01011  -0.0991   0.9588   0.0208
  -5.000  -0.0749   0.01251   0.00820  -0.0989   0.9535   0.0222
  -4.750  -0.0458   0.01227   0.00795  -0.0992   0.9488   0.0231
  -4.500  -0.0136   0.01183   0.00745  -0.1000   0.9450   0.0241
  -4.250   0.0136   0.01127   0.00679  -0.0998   0.9388   0.0250
  -4.000   0.0433   0.01090   0.00634  -0.1000   0.9328   0.0260
  -3.750   0.0728   0.01079   0.00616  -0.1001   0.9264   0.0268
  -3.500   0.0991   0.00962   0.00479  -0.0997   0.9187   0.0278
  -3.250   0.1257   0.00886   0.00396  -0.0993   0.9109   0.0289
  -3.000   0.1532   0.00854   0.00360  -0.0991   0.9018   0.0300
  -2.750   0.1794   0.00821   0.00323  -0.0985   0.8913   0.0307
  -2.500   0.2058   0.00791   0.00286  -0.0980   0.8798   0.0313
  -2.250   0.2318   0.00764   0.00252  -0.0973   0.8651   0.0319
  -2.000   0.2573   0.00742   0.00222  -0.0965   0.8435   0.0327
  -1.750   0.2811   0.00734   0.00197  -0.0953   0.7995   0.0338
  -1.500   0.3004   0.00752   0.00180  -0.0931   0.7223   0.0344
  -1.250   0.3217   0.00769   0.00169  -0.0916   0.6633   0.0348
  -1.000   0.3439   0.00781   0.00157  -0.0902   0.6067   0.0353
  -0.750   0.3675   0.00785   0.00140  -0.0892   0.5660   0.0364
  -0.500   0.3925   0.00788   0.00130  -0.0884   0.5413   0.0379
  -0.250   0.4183   0.00788   0.00123  -0.0878   0.5244   0.0405
   0.000   0.4443   0.00789   0.00120  -0.0873   0.5106   0.0443
   0.250   0.4702   0.00784   0.00120  -0.0868   0.4984   0.0768
   0.500   0.4962   0.00780   0.00120  -0.0863   0.4868   0.1115
   0.750   0.5215   0.00757   0.00126  -0.0858   0.4762   0.2333
   1.000   0.5469   0.00745   0.00132  -0.0853   0.4666   0.3186
   1.250   0.5701   0.00703   0.00141  -0.0845   0.4567   0.5364
   1.500   0.6258   0.00615   0.00155  -0.0909   0.4417   1.0000
   1.750   0.6511   0.00626   0.00159  -0.0902   0.4295   1.0000
   2.000   0.6765   0.00637   0.00163  -0.0896   0.4186   1.0000
   2.250   0.7016   0.00649   0.00169  -0.0889   0.4051   1.0000
   2.500   0.7266   0.00664   0.00175  -0.0882   0.3881   1.0000
   2.750   0.7518   0.00678   0.00182  -0.0875   0.3744   1.0000
   3.000   0.7770   0.00693   0.00190  -0.0869   0.3628   1.0000
   3.250   0.8021   0.00708   0.00199  -0.0862   0.3500   1.0000
   3.500   0.8271   0.00725   0.00209  -0.0856   0.3353   1.0000
   3.750   0.8521   0.00743   0.00220  -0.0849   0.3209   1.0000
   4.000   0.8773   0.00759   0.00231  -0.0843   0.3082   1.0000
   4.250   0.9024   0.00777   0.00244  -0.0837   0.2955   1.0000
   4.500   0.9275   0.00794   0.00258  -0.0831   0.2831   1.0000
   4.750   0.9524   0.00814   0.00272  -0.0824   0.2698   1.0000
   5.000   0.9768   0.00839   0.00288  -0.0818   0.2527   1.0000
   5.250   1.0009   0.00867   0.00307  -0.0810   0.2335   1.0000
   5.500   1.0244   0.00900   0.00329  -0.0802   0.2085   1.0000
   5.750   1.0469   0.00944   0.00356  -0.0793   0.1768   1.0000
   6.000   1.0669   0.01013   0.00398  -0.0779   0.1276   1.0000
   6.250   1.0892   0.01060   0.00434  -0.0770   0.1067   1.0000
   6.500   1.1124   0.01096   0.00464  -0.0762   0.0946   1.0000
   6.750   1.1356   0.01132   0.00495  -0.0753   0.0838   1.0000
   7.000   1.1592   0.01164   0.00523  -0.0746   0.0765   1.0000
   7.250   1.1827   0.01195   0.00552  -0.0738   0.0694   1.0000
   7.500   1.2053   0.01234   0.00585  -0.0729   0.0603   1.0000
   7.750   1.2278   0.01273   0.00618  -0.0721   0.0512   1.0000
   8.000   1.2452   0.01360   0.00682  -0.0704   0.0208   1.0000
   8.250   1.2654   0.01420   0.00741  -0.0691   0.0148   1.0000
   8.500   1.2866   0.01467   0.00796  -0.0679   0.0135   1.0000
   8.750   1.3068   0.01521   0.00857  -0.0666   0.0123   1.0000
   9.000   1.3256   0.01588   0.00932  -0.0651   0.0111   1.0000
   9.250   1.3460   0.01635   0.00984  -0.0638   0.0107   1.0000
   9.500   1.3653   0.01689   0.01045  -0.0625   0.0102   1.0000
   9.750   1.3838   0.01748   0.01110  -0.0610   0.0097   1.0000
  10.000   1.4007   0.01815   0.01184  -0.0592   0.0092   1.0000
  10.250   1.4158   0.01892   0.01268  -0.0572   0.0088   1.0000
  10.500   1.4216   0.02029   0.01418  -0.0538   0.0082   1.0000
  10.750   1.4311   0.02111   0.01509  -0.0508   0.0081   1.0000
  11.000   1.4431   0.02174   0.01579  -0.0483   0.0079   1.0000
  11.250   1.4529   0.02250   0.01663  -0.0456   0.0077   1.0000
  11.500   1.4636   0.02323   0.01742  -0.0431   0.0075   1.0000
  11.750   1.4734   0.02403   0.01830  -0.0406   0.0071   1.0000
  12.000   1.4790   0.02510   0.01945  -0.0378   0.0069   1.0000
  12.250   1.4854   0.02616   0.02059  -0.0352   0.0067   1.0000
  12.500   1.4893   0.02743   0.02194  -0.0326   0.0066   1.0000
  12.750   1.4908   0.02894   0.02355  -0.0300   0.0065   1.0000
  13.000   1.4942   0.03040   0.02509  -0.0279   0.0063   1.0000
  13.250   1.4901   0.03256   0.02735  -0.0255   0.0061   1.0000
  13.500   1.4859   0.03493   0.02983  -0.0237   0.0061   1.0000
  13.750   1.4730   0.03840   0.03343  -0.0222   0.0059   1.0000
  14.000   1.4569   0.04272   0.03788  -0.0217   0.0058   1.0000
  14.250   1.4425   0.04735   0.04264  -0.0220   0.0058   1.0000
  14.500   1.4340   0.05161   0.04703  -0.0229   0.0057   1.0000
  14.750   1.4324   0.05524   0.05077  -0.0241   0.0056   1.0000
  15.000   1.4245   0.05980   0.05545  -0.0255   0.0056   1.0000
  15.250   1.4194   0.06416   0.05993  -0.0271   0.0056   1.0000
  15.500   1.4087   0.06924   0.06511  -0.0289   0.0056   1.0000
  15.750   1.4033   0.07382   0.06980  -0.0308   0.0055   1.0000
  16.000   1.3913   0.07926   0.07535  -0.0327   0.0055   1.0000
  16.250   1.3810   0.08461   0.08080  -0.0349   0.0055   1.0000
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