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GOE 377 AIRFOIL (goe377-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 377 AIRFOIL (goe377-il)
Reynolds number: 200,000
Max Cl/Cd: 73.88 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe377-il-200000-n5.txt
Download as CSV file: xf-goe377-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 377 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3567   0.08872   0.08542  -0.0248   1.0000   0.0178
  -7.250  -0.3646   0.08677   0.08355  -0.0233   1.0000   0.0179
  -7.000  -0.3708   0.08471   0.08156  -0.0221   1.0000   0.0181
  -6.500  -0.3737   0.07977   0.07670  -0.0223   0.9990   0.0189
  -6.250  -0.3387   0.07302   0.06986  -0.0346   0.9925   0.0145
  -6.000  -0.3139   0.06780   0.06458  -0.0409   0.9877   0.0142
  -5.500  -0.2567   0.05729   0.05388  -0.0534   0.9776   0.0142
  -5.250  -0.2298   0.05235   0.04882  -0.0581   0.9707   0.0139
  -5.000  -0.1955   0.04695   0.04323  -0.0638   0.9663   0.0137
  -4.750  -0.1664   0.04195   0.03802  -0.0673   0.9588   0.0137
  -4.500  -0.1311   0.03631   0.03205  -0.0713   0.9548   0.0139
  -4.250  -0.1017   0.03160   0.02697  -0.0724   0.9481   0.0151
  -4.000  -0.0738   0.02691   0.02185  -0.0741   0.9433   0.0163
  -3.750  -0.0417   0.02398   0.01852  -0.0754   0.9401   0.0174
  -3.500  -0.0169   0.02140   0.01552  -0.0748   0.9328   0.0188
  -3.250   0.0146   0.01900   0.01260  -0.0752   0.9287   0.0231
  -3.000   0.0446   0.01687   0.00985  -0.0750   0.9236   0.0263
  -2.750   0.0733   0.01628   0.00921  -0.0754   0.9175   0.0311
  -2.500   0.1066   0.01535   0.00794  -0.0762   0.9133   0.0359
  -2.250   0.1332   0.01469   0.00718  -0.0760   0.9056   0.0406
  -2.000   0.1647   0.01404   0.00640  -0.0766   0.9002   0.0432
  -1.750   0.1926   0.01365   0.00589  -0.0764   0.8922   0.0468
  -1.500   0.2230   0.01301   0.00514  -0.0767   0.8857   0.0476
  -1.250   0.2494   0.01250   0.00458  -0.0762   0.8764   0.0481
  -1.000   0.2773   0.01205   0.00406  -0.0760   0.8656   0.0491
  -0.750   0.3039   0.01157   0.00352  -0.0755   0.8512   0.0515
  -0.500   0.3305   0.01124   0.00314  -0.0749   0.8348   0.0558
  -0.250   0.3573   0.01103   0.00285  -0.0744   0.8192   0.0620
   0.000   0.3837   0.01081   0.00261  -0.0739   0.8035   0.0724
   0.250   0.4100   0.01061   0.00242  -0.0734   0.7870   0.0973
   0.500   0.4323   0.00999   0.00239  -0.0724   0.7696   0.3034
   1.250   0.5635   0.00863   0.00220  -0.0825   0.7089   1.0000
   1.500   0.5877   0.00877   0.00219  -0.0816   0.6872   1.0000
   1.750   0.6115   0.00892   0.00221  -0.0806   0.6641   1.0000
   2.000   0.6351   0.00909   0.00227  -0.0796   0.6415   1.0000
   2.250   0.6586   0.00928   0.00234  -0.0786   0.6192   1.0000
   2.500   0.6819   0.00948   0.00244  -0.0776   0.5969   1.0000
   2.750   0.7048   0.00970   0.00255  -0.0765   0.5737   1.0000
   3.000   0.7277   0.00994   0.00270  -0.0754   0.5504   1.0000
   3.250   0.7502   0.01019   0.00287  -0.0743   0.5272   1.0000
   3.500   0.7728   0.01046   0.00305  -0.0732   0.5032   1.0000
   3.750   0.7947   0.01076   0.00325  -0.0720   0.4750   1.0000
   4.000   0.8164   0.01107   0.00349  -0.0708   0.4454   1.0000
   4.250   0.8380   0.01141   0.00373  -0.0696   0.4156   1.0000
   4.500   0.8597   0.01175   0.00400  -0.0685   0.3889   1.0000
   4.750   0.8810   0.01213   0.00431  -0.0673   0.3627   1.0000
   5.000   0.9024   0.01252   0.00464  -0.0661   0.3396   1.0000
   5.250   0.9242   0.01290   0.00499  -0.0651   0.3195   1.0000
   5.500   0.9452   0.01334   0.00537  -0.0639   0.2954   1.0000
   5.750   0.9644   0.01391   0.00576  -0.0625   0.2569   1.0000
   6.000   0.9836   0.01450   0.00621  -0.0612   0.2141   1.0000
   6.250   1.0026   0.01517   0.00669  -0.0598   0.1649   1.0000
   6.500   1.0127   0.01680   0.00764  -0.0573   0.0618   1.0000
   6.750   1.0267   0.01811   0.00870  -0.0552   0.0221   1.0000
   7.000   1.0448   0.01897   0.00963  -0.0535   0.0168   1.0000
   7.250   1.0623   0.01989   0.01076  -0.0517   0.0140   1.0000
   7.500   1.0796   0.02075   0.01186  -0.0499   0.0131   1.0000
   7.750   1.0948   0.02177   0.01308  -0.0478   0.0122   1.0000
   8.000   1.1084   0.02286   0.01432  -0.0456   0.0112   1.0000
   8.250   1.1208   0.02401   0.01557  -0.0434   0.0097   1.0000
   8.500   1.1299   0.02542   0.01710  -0.0407   0.0092   1.0000
   8.750   1.1356   0.02719   0.01900  -0.0375   0.0088   1.0000
   9.000   1.1394   0.02948   0.02140  -0.0342   0.0084   1.0000
   9.250   1.1503   0.03112   0.02317  -0.0318   0.0083   1.0000
   9.500   1.1619   0.03285   0.02507  -0.0297   0.0081   1.0000
   9.750   1.1732   0.03475   0.02715  -0.0276   0.0079   1.0000
  10.000   1.1832   0.03675   0.02936  -0.0254   0.0077   1.0000
  10.250   1.1908   0.03873   0.03158  -0.0231   0.0074   1.0000
  10.500   1.1958   0.04039   0.03352  -0.0207   0.0068   1.0000
  10.750   1.1989   0.04201   0.03529  -0.0185   0.0062   1.0000
  11.000   1.1994   0.04478   0.03833  -0.0161   0.0063   1.0000
  11.250   1.1979   0.04722   0.04098  -0.0141   0.0061   1.0000
  11.500   1.1940   0.04998   0.04394  -0.0123   0.0060   1.0000
  11.750   1.1872   0.05315   0.04736  -0.0108   0.0060   1.0000
  12.000   1.1794   0.05641   0.05081  -0.0098   0.0058   1.0000
  12.250   1.1677   0.06050   0.05518  -0.0094   0.0060   1.0000
  12.500   1.1563   0.06467   0.05953  -0.0097   0.0058   1.0000
  12.750   1.1425   0.06951   0.06461  -0.0107   0.0059   1.0000
  13.000   1.1274   0.07491   0.07023  -0.0127   0.0059   1.0000
  13.250   1.1122   0.08075   0.07626  -0.0153   0.0059   1.0000
  13.500   1.0920   0.08812   0.08388  -0.0193   0.0060   1.0000
  13.750   1.0760   0.09516   0.09109  -0.0234   0.0060   1.0000
  14.000   1.0573   0.10350   0.09960  -0.0285   0.0061   1.0000
  14.250   1.0393   0.11233   0.10858  -0.0340   0.0061   1.0000
  14.500   1.0172   0.12319   0.11962  -0.0407   0.0064   1.0000
  14.750   0.9985   0.13381   0.13034  -0.0471   0.0065   1.0000
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