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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.34 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe379-il-1000000.txt
Download as CSV file: xf-goe379-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2285   0.08556   0.08413  -0.0280   1.0000   0.0071
  -8.250  -0.2275   0.08254   0.08113  -0.0282   1.0000   0.0072
  -8.000  -0.2277   0.07964   0.07825  -0.0281   1.0000   0.0072
  -7.750  -0.2215   0.07600   0.07462  -0.0299   0.9986   0.0072
  -6.500  -0.2307   0.06965   0.06819  -0.0473   0.9744   0.0076
  -6.250  -0.2004   0.06600   0.06451  -0.0534   0.9693   0.0079
  -6.000  -0.1653   0.06180   0.06026  -0.0612   0.9586   0.0083
  -5.750  -0.1277   0.05762   0.05600  -0.0692   0.9429   0.0091
  -5.500  -0.0985   0.05387   0.05212  -0.0745   0.9168   0.0100
  -5.250  -0.0751   0.05073   0.04882  -0.0773   0.8908   0.0109
  -5.000  -0.0528   0.04795   0.04588  -0.0791   0.8696   0.0112
  -4.750  -0.0318   0.04497   0.04276  -0.0804   0.8509   0.0113
  -4.500  -0.0104   0.04190   0.03956  -0.0815   0.8361   0.0113
  -4.250   0.0118   0.03869   0.03619  -0.0824   0.8225   0.0114
  -4.000   0.0343   0.03549   0.03284  -0.0830   0.8099   0.0114
  -3.250   0.0981   0.02279   0.01937  -0.0823   0.7756   0.0103
  -3.000   0.1120   0.01256   0.00807  -0.0783   0.7674   0.0103
  -2.750   0.1362   0.01119   0.00637  -0.0774   0.7566   0.0107
  -2.500   0.1611   0.01014   0.00504  -0.0765   0.7450   0.0111
  -2.250   0.1862   0.00933   0.00399  -0.0758   0.7328   0.0119
  -2.000   0.2106   0.00833   0.00274  -0.0748   0.7201   0.0131
  -1.750   0.2364   0.00801   0.00232  -0.0742   0.7069   0.0148
  -1.500   0.2622   0.00779   0.00200  -0.0736   0.6936   0.0165
  -1.250   0.2878   0.00755   0.00165  -0.0729   0.6798   0.0184
  -1.000   0.3134   0.00739   0.00144  -0.0723   0.6649   0.0254
  -0.750   0.3396   0.00738   0.00139  -0.0719   0.6487   0.0367
  -0.500   0.3656   0.00735   0.00132  -0.0714   0.6316   0.0456
  -0.250   0.3921   0.00745   0.00136  -0.0711   0.6146   0.0492
   0.000   0.4175   0.00738   0.00120  -0.0706   0.5973   0.0548
   0.250   0.4433   0.00742   0.00117  -0.0701   0.5798   0.0597
   0.500   0.4695   0.00748   0.00116  -0.0697   0.5632   0.0629
   0.750   0.4949   0.00744   0.00107  -0.0692   0.5470   0.0710
   1.000   0.5210   0.00749   0.00105  -0.0688   0.5324   0.0764
   1.250   0.5468   0.00749   0.00104  -0.0684   0.5195   0.0899
   1.500   0.5726   0.00749   0.00105  -0.0680   0.5078   0.1139
   1.750   0.5975   0.00739   0.00112  -0.0674   0.4953   0.2087
   2.000   0.7027   0.00597   0.00137  -0.0860   0.4704   1.0000
   2.250   0.7279   0.00609   0.00141  -0.0854   0.4572   1.0000
   2.500   0.7530   0.00621   0.00146  -0.0848   0.4433   1.0000
   2.750   0.7778   0.00635   0.00152  -0.0842   0.4285   1.0000
   3.250   0.8273   0.00665   0.00170  -0.0831   0.3999   1.0000
   3.500   0.8521   0.00679   0.00180  -0.0825   0.3873   1.0000
   3.750   0.8768   0.00694   0.00190  -0.0819   0.3756   1.0000
   4.250   0.9249   0.00735   0.00217  -0.0805   0.3428   1.0000
   4.500   0.9490   0.00755   0.00233  -0.0798   0.3297   1.0000
   4.750   0.9730   0.00775   0.00248  -0.0792   0.3159   1.0000
   5.000   0.9968   0.00796   0.00264  -0.0785   0.2991   1.0000
   5.250   1.0201   0.00822   0.00283  -0.0777   0.2790   1.0000
   5.500   1.0411   0.00868   0.00309  -0.0766   0.2366   1.0000
   5.750   1.0540   0.00988   0.00374  -0.0742   0.1428   1.0000
   6.000   1.0611   0.01171   0.00491  -0.0707   0.0156   1.0000
   6.250   1.0836   0.01203   0.00529  -0.0697   0.0140   1.0000
   6.500   1.1051   0.01243   0.00575  -0.0686   0.0120   1.0000
   6.750   1.1243   0.01307   0.00648  -0.0670   0.0097   1.0000
   7.000   1.1422   0.01381   0.00736  -0.0652   0.0088   1.0000
   7.250   1.1623   0.01429   0.00791  -0.0639   0.0085   1.0000
   7.500   1.1818   0.01481   0.00849  -0.0624   0.0079   1.0000
   7.750   1.1995   0.01547   0.00922  -0.0607   0.0073   1.0000
   8.000   1.2154   0.01624   0.01007  -0.0587   0.0068   1.0000
   8.250   1.2310   0.01699   0.01088  -0.0567   0.0064   1.0000
   8.500   1.2451   0.01780   0.01175  -0.0546   0.0059   1.0000
   8.750   1.2479   0.01940   0.01347  -0.0506   0.0054   1.0000
   9.000   1.2502   0.02103   0.01520  -0.0466   0.0053   1.0000
   9.250   1.2498   0.02285   0.01711  -0.0422   0.0052   1.0000
   9.500   1.2542   0.02479   0.01912  -0.0388   0.0052   1.0000
   9.750   1.2701   0.02440   0.01882  -0.0370   0.0049   1.0000
  10.000   1.2760   0.02607   0.02059  -0.0340   0.0049   1.0000
  10.250   1.2884   0.02655   0.02115  -0.0321   0.0045   1.0000
  10.500   1.2956   0.02813   0.02284  -0.0297   0.0043   1.0000
  10.750   1.3030   0.02994   0.02477  -0.0274   0.0041   1.0000
  11.000   1.3106   0.03203   0.02700  -0.0252   0.0041   1.0000
  11.250   1.3177   0.03471   0.02986  -0.0229   0.0040   1.0000
  11.500   1.3212   0.03908   0.03455  -0.0204   0.0044   1.0000
  14.750   1.0348   0.09537   0.09304  -0.0164   0.0058   1.0000
  15.000   1.0056   0.10292   0.10076  -0.0210   0.0059   1.0000
  15.250   0.9730   0.11051   0.10852  -0.0263   0.0060   1.0000
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