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GOE 8K AIRFOIL (goe08k-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 8K AIRFOIL (goe08k-il)
Reynolds number: 200,000
Max Cl/Cd: 44.43 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe08k-il-200000.txt
Download as CSV file: xf-goe08k-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 8K AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2173   0.10574   0.10211  -0.0998   0.8931   0.0518
  -8.250  -0.2385   0.10080   0.09720  -0.1078   0.8905   0.0532
  -8.000  -0.2738   0.10125   0.09773  -0.0984   0.8817   0.0531
  -7.750  -0.2227   0.09209   0.08881  -0.0891   0.8674   0.0551
  -7.500  -0.2243   0.08976   0.08648  -0.0875   0.8655   0.0559
  -7.250  -0.2312   0.08676   0.08350  -0.0872   0.8639   0.0565
  -7.000  -0.2550   0.08292   0.07966  -0.0875   0.8624   0.0562
  -6.750  -0.2586   0.07967   0.07639  -0.0872   0.8614   0.0575
  -6.500  -0.3509   0.08256   0.07888  -0.0884   0.8628   0.0553
  -6.250  -0.3386   0.08016   0.07645  -0.0882   0.8618   0.0565
  -6.000  -0.3774   0.07995   0.07625  -0.0790   0.8561   0.0560
  -5.750  -0.3827   0.07818   0.07445  -0.0756   0.8539   0.0569
  -5.500  -0.3852   0.07597   0.07216  -0.0731   0.8525   0.0581
  -5.250  -0.3854   0.07334   0.06941  -0.0709   0.8513   0.0599
  -5.000  -0.3800   0.07033   0.06560  -0.0691   0.8492   0.0648
  -4.750  -0.3784   0.06440   0.05959  -0.0674   0.8484   0.0662
  -4.500  -0.4214   0.06811   0.06327  -0.0572   0.8753   0.0658
  -4.250  -0.4150   0.06575   0.06100  -0.0552   0.8754   0.0669
  -4.000  -0.4178   0.06433   0.05959  -0.0511   0.8750   0.0678
  -3.750  -0.4305   0.06280   0.05803  -0.0449   0.8697   0.0685
  -3.500  -0.4153   0.06115   0.05626  -0.0435   0.8659   0.0727
  -3.250  -0.3999   0.05816   0.05272  -0.0414   0.8635   0.0805
  -3.000  -0.3713   0.05684   0.05136  -0.0423   0.8619   0.0841
  -2.750  -0.3613   0.05578   0.04985  -0.0392   0.8610   0.0949
  -2.500  -0.3789   0.05399   0.04805  -0.0317   0.8533   0.0954
  -2.250  -0.3559   0.05318   0.04701  -0.0311   0.8496   0.1098
  -2.000  -0.3043   0.04653   0.03922  -0.0297   0.8305   0.0750
  -1.750  -0.3026   0.04570   0.03815  -0.0250   0.8264   0.0757
  -1.500  -0.2718   0.04395   0.03602  -0.0245   0.8215   0.0751
  -1.250  -0.2457   0.04279   0.03456  -0.0235   0.8140   0.0759
  -1.000  -0.2279   0.04234   0.03383  -0.0215   0.8096   0.0789
  -0.750  -0.1902   0.04115   0.03248  -0.0232   0.8066   0.0803
  -0.500  -0.1410   0.04047   0.03175  -0.0269   0.8046   0.0851
   0.000  -0.1123   0.03999   0.03114  -0.0228   0.7932   0.0879
   0.250  -0.0718   0.03977   0.03084  -0.0250   0.7912   0.0911
   0.500  -0.0258   0.03951   0.03053  -0.0282   0.7899   0.0930
   0.750  -0.0326   0.03948   0.03051  -0.0228   0.7800   0.0934
   1.000   0.0044   0.03914   0.03023  -0.0247   0.7778   0.0985
   1.250   0.0443   0.03901   0.03012  -0.0270   0.7763   0.1018
   1.500   0.0856   0.03898   0.03007  -0.0295   0.7752   0.1059
   1.750   0.3357   0.04027   0.03434  -0.0828   0.7785   1.0000
   2.000   0.3716   0.04023   0.03414  -0.0842   0.7768   1.0000
   2.250   0.4097   0.04014   0.03394  -0.0861   0.7756   1.0000
   2.500   0.4046   0.04101   0.03479  -0.0811   0.7650   1.0000
   2.750   0.4390   0.04091   0.03461  -0.0824   0.7629   1.0000
   3.000   0.4754   0.04079   0.03442  -0.0840   0.7615   1.0000
   3.250   0.4756   0.04162   0.03524  -0.0799   0.7512   1.0000
   3.500   0.5090   0.04148   0.03506  -0.0810   0.7488   1.0000
   3.750   0.5451   0.04125   0.03480  -0.0824   0.7473   1.0000
   4.000   0.5824   0.04099   0.03451  -0.0841   0.7462   1.0000
   4.250   0.5808   0.04191   0.03543  -0.0799   0.7346   1.0000
   4.500   0.6158   0.04164   0.03516  -0.0811   0.7329   1.0000
   4.750   0.6530   0.04126   0.03478  -0.0827   0.7317   1.0000
   5.000   0.6544   0.04214   0.03568  -0.0789   0.7201   1.0000
   5.250   0.6893   0.04177   0.03533  -0.0802   0.7184   1.0000
   5.500   0.7261   0.04127   0.03485  -0.0816   0.7171   1.0000
   5.750   0.7631   0.04080   0.03441  -0.0831   0.7161   1.0000
   6.000   0.7637   0.04171   0.03535  -0.0792   0.7037   1.0000
   6.250   0.7760   0.04228   0.03598  -0.0772   0.6950   1.0000
   6.500   0.8046   0.04201   0.03575  -0.0773   0.6909   1.0000
   6.750   0.8402   0.04133   0.03513  -0.0784   0.6890   1.0000
   7.000   0.8839   0.03988   0.03377  -0.0803   0.6878   1.0000
   7.250   0.9280   0.03830   0.03226  -0.0822   0.6869   1.0000
   7.500   0.9780   0.03602   0.03007  -0.0846   0.6862   1.0000
   7.750   0.9852   0.03633   0.03045  -0.0813   0.6737   1.0000
   8.000   1.0060   0.03607   0.03027  -0.0800   0.6663   1.0000
   8.250   1.0783   0.03208   0.02642  -0.0853   0.6718   1.0000
   9.000   1.1263   0.03102   0.02558  -0.0782   0.6299   1.0000
   9.250   1.1545   0.03009   0.02470  -0.0775   0.6114   1.0000
   9.500   1.1719   0.03004   0.02467  -0.0757   0.5854   1.0000
   9.750   1.2235   0.02754   0.02180  -0.0779   0.5237   1.0000
  10.000   1.2294   0.02827   0.02217  -0.0743   0.4684   1.0000
  10.250   1.2192   0.03008   0.02365  -0.0687   0.4123   1.0000
  10.500   1.2024   0.03246   0.02569  -0.0626   0.3503   1.0000
  10.750   1.1845   0.03512   0.02797  -0.0569   0.2882   1.0000
  11.000   1.1634   0.03821   0.03059  -0.0511   0.2196   1.0000
  11.250   1.1431   0.04145   0.03329  -0.0459   0.1411   1.0000
  11.500   1.1302   0.04432   0.03572  -0.0418   0.0913   1.0000
  12.000   1.1241   0.04887   0.04016  -0.0358   0.0649   1.0000
  12.250   1.1254   0.05085   0.04217  -0.0334   0.0585   1.0000
  12.500   1.1296   0.05262   0.04399  -0.0314   0.0542   1.0000
  12.750   1.1292   0.05479   0.04615  -0.0289   0.0506   1.0000
  13.000   1.1373   0.05629   0.04774  -0.0273   0.0474   1.0000
  13.250   1.1448   0.05781   0.04930  -0.0257   0.0451   1.0000
  13.500   1.1504   0.05945   0.05090  -0.0241   0.0423   1.0000
  13.750   1.1615   0.06065   0.05217  -0.0226   0.0407   1.0000
  14.000   1.1742   0.06175   0.05337  -0.0213   0.0391   1.0000
  14.250   1.1880   0.06277   0.05446  -0.0201   0.0376   1.0000
  14.500   1.2023   0.06378   0.05549  -0.0189   0.0360   1.0000
  14.750   1.2253   0.06426   0.05593  -0.0182   0.0336   1.0000
  15.000   1.2397   0.06547   0.05733  -0.0171   0.0326   1.0000
  15.250   1.2561   0.06665   0.05869  -0.0161   0.0316   1.0000
  15.500   1.2722   0.06799   0.06020  -0.0152   0.0308   1.0000
  15.750   1.2868   0.06956   0.06193  -0.0142   0.0299   1.0000
  16.000   1.2977   0.07135   0.06386  -0.0131   0.0292   1.0000
  16.250   1.3076   0.07345   0.06613  -0.0120   0.0288   1.0000
  16.500   1.3308   0.07605   0.06881  -0.0121   0.0274   1.0000
  16.750   1.3185   0.07933   0.07237  -0.0098   0.0271   1.0000
  17.000   1.3135   0.08288   0.07619  -0.0081   0.0271   1.0000
  17.250   1.3002   0.08653   0.08011  -0.0063   0.0270   1.0000
  17.500   1.2875   0.09065   0.08449  -0.0048   0.0270   1.0000
  17.750   1.2766   0.09482   0.08889  -0.0037   0.0271   1.0000
  18.000   1.2625   0.09957   0.09387  -0.0027   0.0272   1.0000
  18.250   1.2453   0.10448   0.09900  -0.0022   0.0273   1.0000
  18.500   1.2301   0.10941   0.10415  -0.0020   0.0274   1.0000
  18.750   1.2131   0.11389   0.10883  -0.0023   0.0275   1.0000
  19.000   1.1920   0.11915   0.11431  -0.0032   0.0277   1.0000
  19.250   1.1577   0.12702   0.12252  -0.0057   0.0282   1.0000
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