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GOE 585 AIRFOIL (goe585-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 585 AIRFOIL (goe585-il)
Reynolds number: 500,000
Max Cl/Cd: 90.42 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe585-il-500000.txt
Download as CSV file: xf-goe585-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 585 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4091   0.08559   0.08331  -0.0273   1.0000   0.0263
  -8.250  -0.4095   0.08311   0.08085  -0.0273   1.0000   0.0269
  -8.000  -0.4143   0.08059   0.07837  -0.0269   1.0000   0.0276
  -7.750  -0.4261   0.07832   0.07616  -0.0257   1.0000   0.0282
  -7.500  -0.4358   0.07505   0.07294  -0.0263   1.0000   0.0291
  -7.000  -0.3867   0.04448   0.04243  -0.0449   0.9942   0.0318
  -6.750  -0.3665   0.04193   0.03985  -0.0468   0.9910   0.0326
  -6.500  -0.3436   0.03834   0.03620  -0.0506   0.9876   0.0336
  -6.250  -0.3184   0.03305   0.03079  -0.0565   0.9848   0.0358
  -6.000  -0.3550   0.02509   0.02094  -0.0634   0.9822   0.0317
  -5.750  -0.3305   0.02162   0.01702  -0.0639   0.9775   0.0318
  -5.500  -0.3000   0.01954   0.01472  -0.0653   0.9746   0.0329
  -5.250  -0.2655   0.01884   0.01400  -0.0670   0.9727   0.0345
  -5.000  -0.2311   0.01717   0.01204  -0.0686   0.9711   0.0353
  -4.750  -0.2044   0.01586   0.01050  -0.0684   0.9656   0.0359
  -4.500  -0.1711   0.01488   0.00936  -0.0695   0.9625   0.0371
  -4.250  -0.1356   0.01401   0.00834  -0.0709   0.9603   0.0380
  -4.000  -0.0975   0.01312   0.00732  -0.0729   0.9586   0.0386
  -3.750  -0.0630   0.01241   0.00652  -0.0740   0.9532   0.0390
  -3.500  -0.0292   0.01121   0.00522  -0.0751   0.9471   0.0403
  -3.250   0.0063   0.01041   0.00437  -0.0765   0.9422   0.0417
  -3.000   0.0352   0.00994   0.00388  -0.0764   0.9329   0.0429
  -2.750   0.0668   0.00952   0.00343  -0.0769   0.9243   0.0442
  -2.500   0.0977   0.00917   0.00303  -0.0772   0.9144   0.0456
  -2.250   0.1251   0.00891   0.00273  -0.0768   0.9027   0.0472
  -2.000   0.1529   0.00869   0.00247  -0.0765   0.8912   0.0494
  -1.750   0.1803   0.00842   0.00219  -0.0761   0.8793   0.0547
  -1.500   0.2072   0.00822   0.00199  -0.0756   0.8664   0.0662
  -1.250   0.2331   0.00795   0.00186  -0.0750   0.8520   0.1151
  -1.000   0.2590   0.00779   0.00177  -0.0743   0.8367   0.1481
  -0.750   0.2845   0.00762   0.00167  -0.0737   0.8198   0.1859
  -0.500   0.3090   0.00734   0.00164  -0.0729   0.8013   0.2805
  -0.250   0.3333   0.00708   0.00161  -0.0721   0.7827   0.3788
   0.000   0.3494   0.00619   0.00160  -0.0697   0.7644   0.6837
   0.250   0.4203   0.00571   0.00170  -0.0783   0.7437   0.9843
   0.500   0.4710   0.00582   0.00166  -0.0832   0.7226   1.0000
   0.750   0.4940   0.00595   0.00165  -0.0819   0.7027   1.0000
   1.000   0.5171   0.00606   0.00166  -0.0808   0.6813   1.0000
   1.250   0.5401   0.00619   0.00167  -0.0795   0.6593   1.0000
   1.500   0.5630   0.00632   0.00170  -0.0783   0.6348   1.0000
   1.750   0.5853   0.00649   0.00173  -0.0770   0.6048   1.0000
   2.000   0.6067   0.00671   0.00178  -0.0755   0.5656   1.0000
   2.250   0.6269   0.00702   0.00185  -0.0738   0.5133   1.0000
   2.500   0.6468   0.00741   0.00197  -0.0721   0.4626   1.0000
   2.750   0.6681   0.00774   0.00212  -0.0707   0.4258   1.0000
   3.000   0.6903   0.00804   0.00227  -0.0695   0.3989   1.0000
   3.250   0.7131   0.00830   0.00243  -0.0684   0.3770   1.0000
   3.500   0.7360   0.00856   0.00259  -0.0674   0.3584   1.0000
   3.750   0.7592   0.00881   0.00275  -0.0664   0.3414   1.0000
   4.000   0.7826   0.00904   0.00292  -0.0654   0.3265   1.0000
   4.250   0.8063   0.00927   0.00311  -0.0645   0.3131   1.0000
   4.500   0.8301   0.00949   0.00329  -0.0637   0.3007   1.0000
   4.750   0.8539   0.00972   0.00348  -0.0628   0.2874   1.0000
   5.000   0.8776   0.00996   0.00368  -0.0620   0.2740   1.0000
   5.250   0.9014   0.01020   0.00388  -0.0611   0.2622   1.0000
   5.500   0.9249   0.01046   0.00410  -0.0603   0.2511   1.0000
   5.750   0.9488   0.01069   0.00431  -0.0595   0.2406   1.0000
   6.000   0.9729   0.01092   0.00456  -0.0587   0.2318   1.0000
   6.250   0.9962   0.01121   0.00481  -0.0579   0.2224   1.0000
   6.500   1.0201   0.01144   0.00503  -0.0571   0.2113   1.0000
   6.750   1.0440   0.01168   0.00528  -0.0564   0.2007   1.0000
   7.000   1.0674   0.01196   0.00555  -0.0556   0.1897   1.0000
   7.250   1.0905   0.01226   0.00583  -0.0547   0.1785   1.0000
   7.500   1.1134   0.01258   0.00612  -0.0539   0.1666   1.0000
   7.750   1.1362   0.01292   0.00644  -0.0530   0.1524   1.0000
   8.000   1.1584   0.01330   0.00679  -0.0521   0.1329   1.0000
   8.250   1.1781   0.01393   0.00725  -0.0508   0.1030   1.0000
   8.500   1.1955   0.01477   0.00790  -0.0493   0.0756   1.0000
   8.750   1.2139   0.01550   0.00856  -0.0478   0.0589   1.0000
   9.000   1.2306   0.01639   0.00936  -0.0461   0.0426   1.0000
   9.250   1.2476   0.01722   0.01014  -0.0444   0.0310   1.0000
   9.500   1.2639   0.01808   0.01101  -0.0426   0.0260   1.0000
   9.750   1.2813   0.01878   0.01177  -0.0410   0.0234   1.0000
  10.000   1.2933   0.01987   0.01290  -0.0386   0.0210   1.0000
  10.250   1.3096   0.02055   0.01369  -0.0368   0.0201   1.0000
  10.500   1.3240   0.02130   0.01451  -0.0348   0.0188   1.0000
  10.750   1.3345   0.02213   0.01540  -0.0322   0.0177   1.0000
  11.000   1.3392   0.02325   0.01659  -0.0287   0.0170   1.0000
  11.250   1.3365   0.02484   0.01829  -0.0245   0.0163   1.0000
  11.500   1.3451   0.02580   0.01935  -0.0221   0.0160   1.0000
  11.750   1.3518   0.02691   0.02057  -0.0196   0.0155   1.0000
  12.000   1.3557   0.02827   0.02205  -0.0170   0.0152   1.0000
  12.250   1.3600   0.02966   0.02355  -0.0147   0.0147   1.0000
  12.500   1.3620   0.03131   0.02530  -0.0125   0.0143   1.0000
  12.750   1.3644   0.03302   0.02710  -0.0107   0.0140   1.0000
  13.000   1.3645   0.03504   0.02922  -0.0090   0.0137   1.0000
  13.250   1.3637   0.03727   0.03153  -0.0077   0.0133   1.0000
  13.500   1.3600   0.03996   0.03432  -0.0066   0.0131   1.0000
  13.750   1.3533   0.04316   0.03763  -0.0058   0.0128   1.0000
  14.000   1.3439   0.04690   0.04151  -0.0052   0.0125   1.0000
  14.250   1.3433   0.04976   0.04451  -0.0054   0.0123   1.0000
  14.500   1.3402   0.05307   0.04797  -0.0057   0.0122   1.0000
  14.750   1.3359   0.05667   0.05171  -0.0063   0.0121   1.0000
  15.000   1.3305   0.06058   0.05578  -0.0072   0.0120   1.0000
  15.250   1.3239   0.06483   0.06018  -0.0085   0.0118   1.0000
  15.500   1.3169   0.06937   0.06486  -0.0102   0.0117   1.0000
  15.750   1.3085   0.07429   0.06992  -0.0121   0.0116   1.0000
  16.000   1.3000   0.07941   0.07518  -0.0144   0.0115   1.0000
  16.250   1.2898   0.08499   0.08091  -0.0169   0.0115   1.0000
  16.500   1.2791   0.09086   0.08694  -0.0198   0.0114   1.0000
  16.750   1.2670   0.09712   0.09334  -0.0230   0.0114   1.0000
  17.000   1.2559   0.10342   0.09978  -0.0264   0.0113   1.0000
  17.250   1.2415   0.11049   0.10701  -0.0302   0.0113   1.0000
  17.500   1.2279   0.11762   0.11428  -0.0343   0.0112   1.0000
  17.750   1.2119   0.12545   0.12226  -0.0388   0.0113   1.0000
  18.000   1.1961   0.13356   0.13053  -0.0437   0.0113   1.0000
  18.250   1.1782   0.14238   0.13950  -0.0490   0.0114   1.0000
  18.500   1.1583   0.15211   0.14939  -0.0551   0.0115   1.0000
  18.750   1.1342   0.16348   0.16091  -0.0622   0.0116   1.0000
  19.000   1.1021   0.17798   0.17557  -0.0712   0.0119   1.0000
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