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GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 595 AIRFOIL (goe595-il)
Reynolds number: 50,000
Max Cl/Cd: 36.89 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe595-il-50000.txt
Download as CSV file: xf-goe595-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 595 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3998   0.09799   0.09138  -0.0219   1.0000   0.2611
  -7.750  -0.3956   0.09473   0.08819  -0.0204   1.0000   0.2714
  -7.500  -0.4313   0.09511   0.08881  -0.0186   1.0000   0.2781
  -7.250  -0.4263   0.09183   0.08558  -0.0163   1.0000   0.2922
  -7.000  -0.4297   0.08930   0.08315  -0.0136   1.0000   0.3066
  -6.750  -0.4339   0.08691   0.08085  -0.0108   1.0000   0.3211
  -6.500  -0.4459   0.08505   0.07911  -0.0082   1.0000   0.3366
  -6.250  -0.4278   0.08136   0.07541  -0.0044   1.0000   0.3618
  -6.000  -0.4521   0.08035   0.07455  -0.0011   1.0000   0.3808
  -5.750  -0.4411   0.07729   0.07153   0.0030   1.0000   0.4084
  -4.500  -0.4207   0.04790   0.04055  -0.0304   1.0000   0.1586
  -4.250  -0.4000   0.04322   0.03530  -0.0308   1.0000   0.1403
  -4.000  -0.3778   0.03939   0.03070  -0.0306   1.0000   0.1298
  -3.750  -0.3567   0.03655   0.02740  -0.0298   1.0000   0.1283
  -3.500  -0.3342   0.03423   0.02453  -0.0290   1.0000   0.1300
  -3.250  -0.3104   0.03213   0.02190  -0.0281   1.0000   0.1313
  -3.000  -0.2857   0.03026   0.01953  -0.0271   1.0000   0.1330
  -2.750  -0.2634   0.02869   0.01795  -0.0262   1.0000   0.1419
  -2.500  -0.2397   0.02737   0.01639  -0.0252   1.0000   0.1515
  -2.250  -0.2139   0.02613   0.01498  -0.0243   1.0000   0.1635
  -2.000  -0.1896   0.02511   0.01397  -0.0234   1.0000   0.1894
  -1.750  -0.1287   0.01988   0.01220  -0.0264   1.0000   1.0000
  -1.500  -0.1099   0.02009   0.01179  -0.0251   1.0000   1.0000
  -1.250  -0.0917   0.02034   0.01157  -0.0240   1.0000   1.0000
  -1.000  -0.0735   0.02062   0.01150  -0.0230   1.0000   1.0000
  -0.750  -0.0555   0.02094   0.01153  -0.0220   1.0000   1.0000
  -0.500  -0.0375   0.02131   0.01161  -0.0212   1.0000   1.0000
  -0.250  -0.0198   0.02172   0.01179  -0.0203   1.0000   1.0000
   0.000  -0.0023   0.02218   0.01205  -0.0196   1.0000   1.0000
   0.250   0.0150   0.02270   0.01239  -0.0188   1.0000   1.0000
   0.500   0.0317   0.02327   0.01282  -0.0182   1.0000   1.0000
   0.750   0.0480   0.02392   0.01332  -0.0176   1.0000   1.0000
   1.000   0.0638   0.02463   0.01392  -0.0171   1.0000   1.0000
   1.250   0.0972   0.02581   0.01498  -0.0202   0.9923   1.0000
   1.500   0.1528   0.02735   0.01641  -0.0272   0.9732   1.0000
   1.750   0.2026   0.02860   0.01757  -0.0329   0.9538   1.0000
   2.000   0.2486   0.02968   0.01861  -0.0376   0.9340   1.0000
   2.250   0.2990   0.03073   0.01965  -0.0428   0.9156   1.0000
   2.500   0.3351   0.03152   0.02045  -0.0454   0.8951   1.0000
   2.750   0.3777   0.03226   0.02122  -0.0487   0.8756   1.0000
   3.000   0.4234   0.03273   0.02176  -0.0520   0.8546   1.0000
   3.250   0.4698   0.03284   0.02195  -0.0548   0.8317   1.0000
   3.500   0.5122   0.03284   0.02205  -0.0567   0.8097   1.0000
   3.750   0.5567   0.03270   0.02208  -0.0588   0.7900   1.0000
   4.000   0.6093   0.03220   0.02176  -0.0617   0.7729   1.0000
   4.250   0.6420   0.03222   0.02196  -0.0619   0.7530   1.0000
   4.500   0.6862   0.03172   0.02166  -0.0632   0.7341   1.0000
   4.750   0.7380   0.03074   0.02091  -0.0650   0.7164   1.0000
   5.000   0.7710   0.03054   0.02093  -0.0646   0.6947   1.0000
   5.250   0.8182   0.02965   0.02027  -0.0655   0.6737   1.0000
   5.500   0.8497   0.02957   0.02037  -0.0647   0.6496   1.0000
   5.750   0.8897   0.02917   0.02020  -0.0648   0.6260   1.0000
   6.000   0.9210   0.02933   0.02051  -0.0641   0.6018   1.0000
   6.250   0.9544   0.02883   0.02009  -0.0628   0.5720   1.0000
   6.500   0.9778   0.02846   0.01973  -0.0600   0.5374   1.0000
   6.750   1.0004   0.02826   0.01958  -0.0574   0.5041   1.0000
   7.000   1.0222   0.02811   0.01940  -0.0547   0.4706   1.0000
   7.250   1.0317   0.02810   0.01944  -0.0504   0.4325   1.0000
   7.500   1.0356   0.02807   0.01941  -0.0453   0.3894   1.0000
   7.750   1.0295   0.02829   0.01959  -0.0388   0.3345   1.0000
   8.000   1.0150   0.02949   0.02019  -0.0316   0.2577   1.0000
   8.250   1.0088   0.03207   0.02202  -0.0266   0.1896   1.0000
   8.500   1.0162   0.03418   0.02378  -0.0236   0.1568   1.0000
   8.750   1.0324   0.03617   0.02571  -0.0216   0.1355   1.0000
   9.000   1.0562   0.03843   0.02783  -0.0209   0.1200   1.0000
   9.250   1.0922   0.04134   0.03085  -0.0214   0.1092   1.0000
   9.500   1.1208   0.04452   0.03419  -0.0214   0.1011   1.0000
   9.750   1.1460   0.04807   0.03812  -0.0208   0.0974   1.0000
  10.000   1.1657   0.05180   0.04218  -0.0198   0.0949   1.0000
  10.250   1.1806   0.05620   0.04677  -0.0188   0.0922   1.0000
  10.500   1.1767   0.05958   0.05067  -0.0154   0.0914   1.0000
  10.750   1.1701   0.06321   0.05473  -0.0122   0.0911   1.0000
  11.000   1.1593   0.06704   0.05892  -0.0090   0.0911   1.0000
  11.250   1.1477   0.07095   0.06309  -0.0061   0.0915   1.0000
  11.500   1.1358   0.07516   0.06750  -0.0037   0.0921   1.0000
  11.750   1.1203   0.07924   0.07183  -0.0017   0.0929   1.0000
  12.000   1.0376   0.08459   0.07764  -0.0011   0.0971   1.0000
  12.250   0.9944   0.09290   0.08605  -0.0048   0.1009   1.0000
  12.500   0.9695   0.10076   0.09396  -0.0085   0.1033   1.0000
  12.750   0.9549   0.10816   0.10137  -0.0117   0.1047   1.0000
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