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GOE 115 (MVA MK.2) AIRFOIL (goe115-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 115 (MVA MK.2) AIRFOIL (goe115-il)
Reynolds number: 200,000
Max Cl/Cd: 76.73 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe115-il-200000-n5.txt
Download as CSV file: xf-goe115-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 115 (MVA MK.2) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3861   0.08852   0.08508  -0.0398   1.0000   0.0144
  -9.000  -0.3894   0.08431   0.08093  -0.0413   1.0000   0.0144
  -8.750  -0.3952   0.07988   0.07657  -0.0428   1.0000   0.0142
  -8.500  -0.4043   0.07535   0.07212  -0.0441   1.0000   0.0141
  -8.250  -0.4186   0.07094   0.06781  -0.0448   1.0000   0.0139
  -8.000  -0.4391   0.06610   0.06310  -0.0455   1.0000   0.0137
  -7.750  -0.4380   0.04144   0.03777  -0.0782   0.9743   0.0128
  -7.500  -0.4156   0.03630   0.03217  -0.0839   0.9627   0.0131
  -7.250  -0.3902   0.03257   0.02800  -0.0874   0.9520   0.0138
  -7.000  -0.3635   0.02980   0.02477  -0.0897   0.9409   0.0152
  -6.750  -0.3359   0.02671   0.02104  -0.0914   0.9300   0.0169
  -6.500  -0.3066   0.02424   0.01793  -0.0925   0.9198   0.0179
  -6.250  -0.2787   0.02196   0.01539  -0.0936   0.9094   0.0191
  -6.000  -0.2504   0.02100   0.01430  -0.0944   0.8975   0.0212
  -5.750  -0.2221   0.01978   0.01279  -0.0947   0.8854   0.0234
  -5.500  -0.1939   0.01872   0.01141  -0.0947   0.8733   0.0255
  -5.250  -0.1673   0.01758   0.01004  -0.0947   0.8612   0.0280
  -5.000  -0.1416   0.01650   0.00890  -0.0945   0.8493   0.0302
  -4.500  -0.0897   0.01521   0.00733  -0.0938   0.8253   0.0349
  -4.250  -0.0640   0.01465   0.00664  -0.0933   0.8131   0.0358
  -4.000  -0.0395   0.01390   0.00579  -0.0929   0.8011   0.0378
  -3.750  -0.0138   0.01345   0.00520  -0.0925   0.7892   0.0401
  -3.500   0.0125   0.01312   0.00471  -0.0922   0.7776   0.0413
  -3.250   0.0390   0.01286   0.00425  -0.0919   0.7663   0.0425
  -3.000   0.0657   0.01264   0.00388  -0.0915   0.7549   0.0439
  -2.750   0.0924   0.01246   0.00355  -0.0913   0.7441   0.0455
  -2.500   0.1192   0.01228   0.00326  -0.0910   0.7338   0.0490
  -2.250   0.1458   0.01209   0.00302  -0.0907   0.7232   0.0561
  -2.000   0.1707   0.01140   0.00274  -0.0905   0.7132   0.1781
  -1.750   0.1970   0.01126   0.00276  -0.0902   0.7040   0.2422
  -1.500   0.2241   0.01127   0.00270  -0.0900   0.6952   0.2656
  -1.250   0.2512   0.01129   0.00265  -0.0898   0.6872   0.2760
  -1.000   0.2783   0.01131   0.00261  -0.0896   0.6799   0.2866
  -0.750   0.3054   0.01133   0.00259  -0.0895   0.6730   0.2976
  -0.500   0.3324   0.01136   0.00258  -0.0893   0.6663   0.3098
  -0.250   0.3594   0.01139   0.00260  -0.0892   0.6601   0.3238
   0.000   0.3864   0.01140   0.00261  -0.0890   0.6538   0.3325
   0.250   0.4134   0.01143   0.00262  -0.0888   0.6489   0.3407
   0.500   0.4405   0.01145   0.00267  -0.0887   0.6434   0.3495
   0.750   0.4673   0.01145   0.00274  -0.0886   0.6385   0.3666
   1.000   0.4939   0.01144   0.00280  -0.0884   0.6337   0.3877
   1.250   0.5204   0.01142   0.00288  -0.0881   0.6272   0.4035
   1.500   0.5469   0.01144   0.00295  -0.0879   0.6213   0.4180
   1.750   0.5732   0.01141   0.00305  -0.0876   0.6153   0.4419
   2.000   0.5990   0.01131   0.00318  -0.0873   0.6099   0.4954
   2.250   0.6219   0.01084   0.00333  -0.0862   0.6050   0.6930
   2.500   0.6712   0.01046   0.00347  -0.0907   0.5982   1.0000
   2.750   0.6977   0.01061   0.00359  -0.0904   0.5926   1.0000
   3.000   0.7241   0.01075   0.00377  -0.0901   0.5868   1.0000
   3.250   0.7505   0.01089   0.00396  -0.0898   0.5816   1.0000
   3.500   0.7771   0.01106   0.00415  -0.0896   0.5774   1.0000
   3.750   0.8034   0.01122   0.00440  -0.0893   0.5721   1.0000
   4.000   0.8289   0.01135   0.00456  -0.0888   0.5622   1.0000
   4.250   0.8535   0.01147   0.00471  -0.0880   0.5478   1.0000
   4.500   0.8770   0.01156   0.00484  -0.0870   0.5251   1.0000
   4.750   0.8985   0.01171   0.00494  -0.0857   0.4885   1.0000
   5.000   0.9179   0.01204   0.00508  -0.0840   0.4189   1.0000
   5.250   0.9244   0.01348   0.00572  -0.0806   0.2855   1.0000
   5.500   0.9181   0.01637   0.00729  -0.0760   0.0595   1.0000
   5.750   0.9348   0.01729   0.00815  -0.0742   0.0348   1.0000
   6.000   0.9531   0.01805   0.00900  -0.0727   0.0271   1.0000
   6.250   0.9699   0.01889   0.00991  -0.0709   0.0224   1.0000
   6.500   0.9864   0.01970   0.01082  -0.0692   0.0198   1.0000
   6.750   1.0010   0.02060   0.01186  -0.0671   0.0182   1.0000
   7.000   1.0133   0.02163   0.01299  -0.0648   0.0170   1.0000
   7.250   1.0244   0.02269   0.01414  -0.0623   0.0158   1.0000
   7.500   1.0339   0.02372   0.01523  -0.0596   0.0146   1.0000
   7.750   1.0403   0.02502   0.01657  -0.0566   0.0135   1.0000
   8.000   1.0430   0.02719   0.01886  -0.0532   0.0124   1.0000
   8.250   1.0572   0.02855   0.02030  -0.0514   0.0121   1.0000
   8.500   1.0742   0.03006   0.02192  -0.0499   0.0117   1.0000
   8.750   1.0943   0.03176   0.02375  -0.0489   0.0114   1.0000
   9.000   1.1166   0.03368   0.02584  -0.0481   0.0108   1.0000
   9.250   1.1347   0.03529   0.02761  -0.0470   0.0101   1.0000
   9.500   1.1489   0.03674   0.02922  -0.0455   0.0094   1.0000
   9.750   1.1625   0.03849   0.03113  -0.0441   0.0090   1.0000
  10.000   1.1731   0.04036   0.03317  -0.0424   0.0086   1.0000
  10.250   1.1832   0.04272   0.03578  -0.0407   0.0084   1.0000
  10.500   1.1898   0.04523   0.03852  -0.0389   0.0083   1.0000
  10.750   1.1922   0.04798   0.04149  -0.0369   0.0081   1.0000
  11.000   1.1915   0.05098   0.04475  -0.0349   0.0081   1.0000
  11.250   1.1868   0.05426   0.04827  -0.0329   0.0080   1.0000
  11.500   1.1793   0.05772   0.05199  -0.0312   0.0080   1.0000
  11.750   1.1689   0.06149   0.05600  -0.0299   0.0080   1.0000
  12.000   1.1587   0.06516   0.05991  -0.0290   0.0080   1.0000
  12.250   1.1438   0.06965   0.06463  -0.0287   0.0080   1.0000
  12.500   1.1291   0.07427   0.06946  -0.0289   0.0080   1.0000
  12.750   1.1156   0.07890   0.07431  -0.0297   0.0080   1.0000
  13.000   1.0986   0.08437   0.07998  -0.0312   0.0080   1.0000
  13.250   1.0813   0.09026   0.08608  -0.0333   0.0081   1.0000
  13.500   1.0621   0.09698   0.09300  -0.0363   0.0082   1.0000
  13.750   1.0400   0.10498   0.10120  -0.0403   0.0084   1.0000
  14.000   1.0180   0.11374   0.11014  -0.0453   0.0084   1.0000
  14.250   0.9789   0.12958   0.12622  -0.0552   0.0089   1.0000
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