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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 50,000
Max Cl/Cd: 38.4 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe330-il-50000-n5.txt
Download as CSV file: xf-goe330-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 330 (PFALZ 59) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3141   0.11389   0.10781  -0.0270   1.0000   0.0886
  -7.750  -0.3331   0.11375   0.10780  -0.0248   1.0000   0.0893
  -7.500  -0.3511   0.11346   0.10764  -0.0237   1.0000   0.0899
  -7.250  -0.3500   0.11123   0.10549  -0.0290   0.9956   0.0907
  -7.000  -0.3316   0.10543   0.09965  -0.0241   0.9947   0.0946
  -6.750  -0.3149   0.10173   0.09593  -0.0282   0.9879   0.0987
  -6.500  -0.2952   0.09883   0.09297  -0.0407   0.9768   0.1038
  -6.250  -0.2787   0.09428   0.08843  -0.0440   0.9703   0.1056
  -6.000  -0.2619   0.09032   0.08447  -0.0431   0.9654   0.1102
  -5.500  -0.2223   0.08315   0.07722  -0.0524   0.9505   0.1250
  -5.000  -0.1789   0.07615   0.07011  -0.0612   0.9354   0.1401
  -4.750  -0.1556   0.07293   0.06675  -0.0673   0.9263   0.1514
  -4.500  -0.1282   0.06960   0.06332  -0.0717   0.9199   0.1661
  -4.000  -0.0887   0.06408   0.05776  -0.0734   0.9056   0.2025
  -3.500   0.0182   0.05228   0.04463  -0.0933   0.8916   0.0881
  -3.250   0.0536   0.04915   0.04120  -0.0966   0.8844   0.0858
  -3.000   0.0916   0.04626   0.03792  -0.0999   0.8758   0.0858
  -2.750   0.1274   0.04355   0.03479  -0.1023   0.8662   0.0833
  -2.500   0.1733   0.04064   0.03123  -0.1059   0.8594   0.0801
  -2.250   0.2063   0.03879   0.02883  -0.1069   0.8491   0.0787
  -2.000   0.2495   0.03678   0.02635  -0.1096   0.8436   0.0785
  -1.750   0.2750   0.03559   0.02505  -0.1095   0.8333   0.0808
  -1.500   0.3155   0.03412   0.02327  -0.1116   0.8280   0.0844
  -1.250   0.3416   0.03324   0.02212  -0.1112   0.8172   0.0855
  -1.000   0.3824   0.03190   0.02043  -0.1128   0.8119   0.0866
  -0.750   0.4066   0.03128   0.01958  -0.1119   0.8003   0.0879
  -0.500   0.4381   0.03052   0.01855  -0.1119   0.7915   0.0898
  -0.250   0.4720   0.02964   0.01755  -0.1124   0.7830   0.0933
   0.000   0.4988   0.02920   0.01702  -0.1119   0.7720   0.1004
   0.250   0.5358   0.02831   0.01605  -0.1128   0.7650   0.1098
   0.750   0.5867   0.02762   0.01524  -0.1114   0.7409   0.1335
   1.000   0.6193   0.02669   0.01468  -0.1120   0.7316   0.1962
   1.500   0.6738   0.02481   0.01410  -0.1107   0.7081   1.0000
   1.750   0.7002   0.02486   0.01392  -0.1100   0.6959   1.0000
   2.000   0.7288   0.02483   0.01368  -0.1096   0.6845   1.0000
   2.250   0.7607   0.02466   0.01331  -0.1096   0.6743   1.0000
   2.500   0.7864   0.02479   0.01330  -0.1089   0.6611   1.0000
   2.750   0.8128   0.02493   0.01332  -0.1083   0.6484   1.0000
   3.000   0.8401   0.02507   0.01332  -0.1079   0.6361   1.0000
   3.250   0.8690   0.02517   0.01328  -0.1077   0.6246   1.0000
   3.500   0.8977   0.02532   0.01333  -0.1075   0.6131   1.0000
   3.750   0.9213   0.02573   0.01368  -0.1067   0.6001   1.0000
   4.000   0.9456   0.02614   0.01404  -0.1060   0.5880   1.0000
   4.250   0.9719   0.02647   0.01433  -0.1057   0.5771   1.0000
   4.500   0.9970   0.02687   0.01469  -0.1051   0.5663   1.0000
   4.750   1.0181   0.02747   0.01531  -0.1042   0.5548   1.0000
   5.000   1.0423   0.02793   0.01577  -0.1036   0.5448   1.0000
   5.250   1.0671   0.02837   0.01623  -0.1031   0.5353   1.0000
   5.500   1.0870   0.02904   0.01696  -0.1020   0.5249   1.0000
   5.750   1.1115   0.02946   0.01738  -0.1014   0.5156   1.0000
   6.000   1.1337   0.02994   0.01792  -0.1005   0.5053   1.0000
   6.250   1.1526   0.03052   0.01855  -0.0991   0.4939   1.0000
   6.500   1.1739   0.03094   0.01900  -0.0980   0.4827   1.0000
   6.750   1.1986   0.03121   0.01924  -0.0972   0.4722   1.0000
   7.000   1.2163   0.03188   0.02004  -0.0958   0.4612   1.0000
   7.250   1.2361   0.03256   0.02081  -0.0947   0.4518   1.0000
   7.500   1.2611   0.03305   0.02135  -0.0942   0.4436   1.0000
   7.750   1.2770   0.03400   0.02247  -0.0927   0.4347   1.0000
   8.000   1.3045   0.03446   0.02301  -0.0926   0.4272   1.0000
   8.250   1.3164   0.03563   0.02441  -0.0906   0.4182   1.0000
   8.500   1.3423   0.03619   0.02504  -0.0903   0.4105   1.0000
   8.750   1.3525   0.03743   0.02653  -0.0882   0.4014   1.0000
   9.000   1.3740   0.03819   0.02745  -0.0874   0.3934   1.0000
   9.250   1.3846   0.03942   0.02893  -0.0853   0.3845   1.0000
   9.500   1.4021   0.04040   0.03008  -0.0841   0.3768   1.0000
   9.750   1.4113   0.04169   0.03161  -0.0819   0.3682   1.0000
  10.000   1.4159   0.04280   0.03290  -0.0789   0.3580   1.0000
  10.250   1.4210   0.04341   0.03362  -0.0758   0.3452   1.0000
  10.500   1.4197   0.04419   0.03446  -0.0721   0.3313   1.0000
  10.750   1.4107   0.04583   0.03627  -0.0684   0.3189   1.0000
  11.000   1.4011   0.04798   0.03861  -0.0653   0.3077   1.0000
  11.250   1.3962   0.04991   0.04068  -0.0628   0.2966   1.0000
  11.500   1.3927   0.05180   0.04270  -0.0607   0.2852   1.0000
  11.750   1.3834   0.05456   0.04564  -0.0588   0.2736   1.0000
  12.000   1.3714   0.05804   0.04933  -0.0575   0.2625   1.0000
  12.250   1.3625   0.06140   0.05289  -0.0565   0.2519   1.0000
  12.500   1.3523   0.06504   0.05668  -0.0559   0.2397   1.0000
  12.750   1.3402   0.06918   0.06096  -0.0557   0.2262   1.0000
  13.000   1.3287   0.07349   0.06541  -0.0557   0.2128   1.0000
  13.250   1.3165   0.07807   0.07007  -0.0561   0.1976   1.0000
  13.500   1.3047   0.08249   0.07440  -0.0565   0.1766   1.0000
  13.750   1.2906   0.08767   0.07959  -0.0573   0.1574   1.0000
  14.000   1.2747   0.09373   0.08580  -0.0588   0.1399   1.0000
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