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GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 99.8 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe210-il-1000000-n5.txt
Download as CSV file: xf-goe210-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 210 (DAIMLER) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3572   0.10343   0.10182  -0.0198   1.0000   0.0047
  -8.750  -0.3515   0.10040   0.09880  -0.0210   1.0000   0.0043
  -8.500  -0.3466   0.09707   0.09549  -0.0224   1.0000   0.0040
  -8.250  -0.3429   0.09363   0.09207  -0.0236   1.0000   0.0037
  -7.750  -0.3232   0.08546   0.08392  -0.0306   0.9874   0.0036
  -5.750  -0.1505   0.01248   0.00800  -0.0961   0.8237   0.0054
  -5.500  -0.1238   0.01158   0.00686  -0.0960   0.8112   0.0057
  -5.250  -0.0967   0.01094   0.00605  -0.0960   0.8007   0.0061
  -5.000  -0.0693   0.01037   0.00531  -0.0959   0.7916   0.0065
  -4.500  -0.0142   0.00945   0.00410  -0.0958   0.7756   0.0075
  -4.000   0.0413   0.00880   0.00329  -0.0957   0.7617   0.0099
  -3.750   0.0691   0.00852   0.00290  -0.0957   0.7549   0.0109
  -3.500   0.0972   0.00843   0.00282  -0.0956   0.7470   0.0132
  -3.250   0.1250   0.00844   0.00278  -0.0955   0.7381   0.0151
  -3.000   0.1531   0.00837   0.00268  -0.0955   0.7306   0.0166
  -2.750   0.1812   0.00845   0.00275  -0.0954   0.7230   0.0180
  -2.500   0.2092   0.00844   0.00271  -0.0954   0.7141   0.0196
  -2.250   0.2371   0.00841   0.00262  -0.0953   0.7020   0.0215
  -2.000   0.2647   0.00837   0.00248  -0.0952   0.6864   0.0228
  -1.750   0.2924   0.00841   0.00246  -0.0951   0.6722   0.0237
  -1.500   0.3203   0.00839   0.00238  -0.0950   0.6603   0.0241
  -1.250   0.3479   0.00797   0.00187  -0.0950   0.6492   0.0259
  -1.000   0.3758   0.00781   0.00166  -0.0950   0.6386   0.0269
  -0.750   0.4037   0.00771   0.00150  -0.0950   0.6262   0.0275
  -0.500   0.4313   0.00766   0.00136  -0.0949   0.6095   0.0279
  -0.250   0.4589   0.00763   0.00125  -0.0948   0.5910   0.0281
   0.000   0.4863   0.00765   0.00117  -0.0947   0.5660   0.0285
   0.250   0.5134   0.00773   0.00112  -0.0946   0.5365   0.0291
   0.500   0.5401   0.00787   0.00110  -0.0944   0.4974   0.0290
   0.750   0.5656   0.00820   0.00115  -0.0940   0.4341   0.0291
   1.000   0.5902   0.00870   0.00128  -0.0936   0.3516   0.0292
   1.250   0.6159   0.00903   0.00138  -0.0933   0.2996   0.0295
   1.500   0.6426   0.00922   0.00144  -0.0932   0.2701   0.0301
   1.750   0.6691   0.00944   0.00153  -0.0930   0.2395   0.0313
   2.000   0.6954   0.00967   0.00163  -0.0928   0.2103   0.0340
   2.250   0.7219   0.00983   0.00178  -0.0926   0.1876   0.0780
   2.500   0.7488   0.00987   0.00193  -0.0926   0.1738   0.1651
   3.000   0.7985   0.00853   0.00233  -0.0920   0.1584   1.0000
   3.250   0.8257   0.00867   0.00244  -0.0919   0.1540   1.0000
   3.500   0.8526   0.00884   0.00257  -0.0918   0.1483   1.0000
   3.750   0.8795   0.00901   0.00271  -0.0917   0.1432   1.0000
   4.000   0.9064   0.00917   0.00285  -0.0915   0.1377   1.0000
   4.250   0.9328   0.00938   0.00301  -0.0914   0.1296   1.0000
   4.500   0.9591   0.00961   0.00318  -0.0912   0.1175   1.0000
   4.750   0.9818   0.01033   0.00362  -0.0905   0.0646   1.0000
   5.000   1.0075   0.01061   0.00386  -0.0902   0.0587   1.0000
   5.250   1.0334   0.01087   0.00411  -0.0900   0.0530   1.0000
   5.500   1.0595   0.01108   0.00434  -0.0897   0.0511   1.0000
   5.750   1.0853   0.01133   0.00459  -0.0895   0.0481   1.0000
   6.000   1.1105   0.01164   0.00488  -0.0892   0.0435   1.0000
   6.250   1.1361   0.01190   0.00514  -0.0889   0.0402   1.0000
   6.500   1.1590   0.01249   0.00558  -0.0882   0.0187   1.0000
   6.750   1.1834   0.01289   0.00597  -0.0878   0.0118   1.0000
   7.000   1.2080   0.01324   0.00638  -0.0873   0.0096   1.0000
   7.250   1.2316   0.01373   0.00690  -0.0867   0.0072   1.0000
   7.500   1.2558   0.01409   0.00730  -0.0862   0.0064   1.0000
   7.750   1.2794   0.01453   0.00778  -0.0857   0.0056   1.0000
   8.000   1.3020   0.01508   0.00838  -0.0849   0.0048   1.0000
   8.250   1.3253   0.01552   0.00887  -0.0843   0.0045   1.0000
   8.500   1.3481   0.01599   0.00939  -0.0836   0.0040   1.0000
   8.750   1.3705   0.01649   0.00992  -0.0830   0.0036   1.0000
   9.000   1.3919   0.01709   0.01057  -0.0821   0.0033   1.0000
   9.250   1.4121   0.01781   0.01136  -0.0811   0.0030   1.0000
   9.500   1.4329   0.01841   0.01206  -0.0801   0.0029   1.0000
   9.750   1.4529   0.01907   0.01280  -0.0791   0.0027   1.0000
  10.000   1.4721   0.01978   0.01358  -0.0779   0.0025   1.0000
  10.250   1.4905   0.02052   0.01440  -0.0767   0.0024   1.0000
  10.500   1.5081   0.02129   0.01525  -0.0754   0.0023   1.0000
  10.750   1.5248   0.02208   0.01611  -0.0740   0.0021   1.0000
  11.000   1.5399   0.02297   0.01708  -0.0723   0.0020   1.0000
  11.250   1.5515   0.02402   0.01823  -0.0702   0.0019   1.0000
  11.500   1.5555   0.02538   0.01972  -0.0669   0.0018   1.0000
  11.750   1.5613   0.02661   0.02109  -0.0640   0.0018   1.0000
  12.000   1.5691   0.02773   0.02231  -0.0617   0.0017   1.0000
  12.250   1.5760   0.02897   0.02366  -0.0594   0.0017   1.0000
  12.500   1.5808   0.03042   0.02523  -0.0572   0.0016   1.0000
  12.750   1.5845   0.03204   0.02697  -0.0551   0.0016   1.0000
  13.000   1.5875   0.03384   0.02889  -0.0533   0.0015   1.0000
  13.250   1.5878   0.03601   0.03119  -0.0517   0.0015   1.0000
  13.500   1.5875   0.03840   0.03371  -0.0504   0.0014   1.0000
  13.750   1.5848   0.04118   0.03663  -0.0494   0.0014   1.0000
  14.000   1.5812   0.04423   0.03982  -0.0487   0.0014   1.0000
  14.250   1.5757   0.04764   0.04337  -0.0483   0.0013   1.0000
  14.500   1.5684   0.05147   0.04733  -0.0483   0.0013   1.0000
  14.750   1.5601   0.05560   0.05161  -0.0487   0.0013   1.0000
  15.000   1.5485   0.06038   0.05655  -0.0495   0.0013   1.0000
  15.250   1.5357   0.06567   0.06199  -0.0508   0.0013   1.0000
  15.500   1.5206   0.07163   0.06809  -0.0527   0.0013   1.0000
  15.750   1.5037   0.07829   0.07491  -0.0553   0.0012   1.0000
  16.000   1.4853   0.08566   0.08242  -0.0584   0.0012   1.0000
  16.250   1.4631   0.09399   0.09091  -0.0621   0.0013   1.0000
  16.500   1.4409   0.10258   0.09965  -0.0660   0.0013   1.0000
  16.750   1.4189   0.11125   0.10846  -0.0700   0.0013   1.0000
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