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GOE 10K AIRFOIL (goe10k-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 10K AIRFOIL (goe10k-il)
Reynolds number: 500,000
Max Cl/Cd: 88.5 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe10k-il-500000.txt
Download as CSV file: xf-goe10k-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 10K 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.5344   0.08801   0.08578  -0.0101   1.0000   0.0074
  -7.500  -0.5382   0.08521   0.08302  -0.0104   1.0000   0.0073
  -7.250  -0.5382   0.08181   0.07965  -0.0119   1.0000   0.0077
  -7.000  -0.5346   0.07814   0.07599  -0.0143   1.0000   0.0076
  -6.750  -0.5294   0.07427   0.07212  -0.0169   1.0000   0.0079
  -6.500  -0.5221   0.07027   0.06811  -0.0195   1.0000   0.0081
  -6.250  -0.5127   0.06610   0.06391  -0.0220   1.0000   0.0084
  -6.000  -0.4989   0.06135   0.05908  -0.0251   1.0000   0.0089
  -5.750  -0.4822   0.05669   0.05433  -0.0275   1.0000   0.0091
  -5.500  -0.4645   0.05218   0.04968  -0.0289   1.0000   0.0092
  -5.250  -0.4499   0.04728   0.04464  -0.0294   1.0000   0.0093
  -5.000  -0.4426   0.04402   0.04131  -0.0290   1.0000   0.0097
  -4.750  -0.4286   0.04106   0.03824  -0.0285   1.0000   0.0104
  -4.500  -0.4110   0.03755   0.03454  -0.0280   1.0000   0.0112
  -4.250  -0.3855   0.03389   0.03056  -0.0266   1.0000   0.0126
  -4.000  -0.3696   0.02905   0.02538  -0.0256   1.0000   0.0132
  -3.750  -0.3534   0.02699   0.02322  -0.0248   1.0000   0.0143
  -3.500  -0.3312   0.02522   0.02121  -0.0233   1.0000   0.0168
  -3.250  -0.3122   0.02189   0.01752  -0.0224   1.0000   0.0210
  -3.000  -0.2864   0.01991   0.01525  -0.0219   0.9995   0.0248
  -2.750  -0.2560   0.01757   0.01250  -0.0222   0.9982   0.0309
  -2.500  -0.2245   0.01386   0.00806  -0.0198   0.9983   0.0129
  -2.250  -0.1968   0.01153   0.00549  -0.0192   0.9977   0.0113
  -2.000  -0.1664   0.01047   0.00426  -0.0194   0.9964   0.0118
  -1.750  -0.1356   0.00974   0.00345  -0.0200   0.9950   0.0157
  -1.500  -0.1050   0.00910   0.00270  -0.0204   0.9928   0.0298
  -1.250  -0.0743   0.00863   0.00257  -0.0213   0.9906   0.1213
  -1.000  -0.0504   0.00720   0.00265  -0.0215   0.9887   0.5696
  -0.750   0.0013   0.00611   0.00266  -0.0267   0.9944   1.0000
  -0.500   0.0379   0.00615   0.00260  -0.0288   0.9912   1.0000
  -0.250   0.0826   0.00620   0.00257  -0.0327   0.9878   1.0000
   0.000   0.1217   0.00616   0.00248  -0.0352   0.9833   1.0000
   0.250   0.1668   0.00609   0.00239  -0.0391   0.9791   1.0000
   0.500   0.2055   0.00599   0.00230  -0.0415   0.9738   1.0000
   0.750   0.2458   0.00589   0.00221  -0.0443   0.9691   1.0000
   1.000   0.2901   0.00561   0.00198  -0.0477   0.9598   1.0000
   1.250   0.3344   0.00528   0.00173  -0.0510   0.9467   1.0000
   1.500   0.3818   0.00503   0.00157  -0.0551   0.9284   1.0000
   1.750   0.4416   0.00499   0.00127  -0.0614   0.8051   1.0000
   2.000   0.4352   0.00698   0.00150  -0.0539   0.3939   1.0000
   2.250   0.4461   0.00850   0.00188  -0.0511   0.1006   1.0000
   2.500   0.4656   0.00939   0.00244  -0.0492   0.0182   1.0000
   2.750   0.4869   0.01009   0.00325  -0.0476   0.0129   1.0000
   3.000   0.5083   0.01084   0.00409  -0.0459   0.0115   1.0000
   3.250   0.5286   0.01192   0.00526  -0.0440   0.0111   1.0000
   3.500   0.5489   0.01359   0.00696  -0.0422   0.0099   1.0000
   3.750   0.5731   0.01511   0.00867  -0.0407   0.0101   1.0000
   4.500   0.6341   0.02760   0.02260  -0.0329   0.0189   1.0000
   4.750   0.6619   0.02708   0.02230  -0.0313   0.0159   1.0000
   5.000   0.6800   0.02916   0.02458  -0.0296   0.0145   1.0000
   5.250   0.6877   0.03444   0.03005  -0.0276   0.0134   1.0000
   5.500   0.7114   0.03632   0.03245  -0.0244   0.0122   1.0000
   5.750   0.7271   0.03963   0.03603  -0.0223   0.0111   1.0000
   6.000   0.7398   0.04264   0.03922  -0.0207   0.0104   1.0000
   6.500   0.7111   0.03835   0.03551  -0.0149   0.0098   1.0000
   6.750   0.7173   0.04314   0.04053  -0.0132   0.0097   1.0000
   7.000   0.7234   0.04839   0.04601  -0.0121   0.0095   1.0000
   7.250   0.7248   0.05388   0.05166  -0.0117   0.0093   1.0000
   7.500   0.7210   0.05906   0.05694  -0.0118   0.0091   1.0000
   7.750   0.7120   0.06404   0.06199  -0.0121   0.0088   1.0000
   8.000   0.6971   0.06822   0.06620  -0.0122   0.0090   1.0000
   8.250   0.6827   0.07269   0.07069  -0.0141   0.0094   1.0000
   8.500   0.6710   0.07800   0.07599  -0.0176   0.0095   1.0000
   8.750   0.6633   0.08336   0.08134  -0.0202   0.0095   1.0000
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