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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 500,000
Max Cl/Cd: 97.27 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe137-il-500000-n5.txt
Download as CSV file: xf-goe137-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 137 (MVA H.15) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3658   0.09414   0.09201  -0.0208   1.0000   0.0073
  -8.500  -0.3632   0.09013   0.08802  -0.0230   1.0000   0.0075
  -8.000  -0.3619   0.08197   0.07993  -0.0275   0.9976   0.0078
  -7.000  -0.3218   0.01721   0.01278  -0.0859   0.9272   0.0117
  -6.750  -0.2963   0.01628   0.01166  -0.0857   0.9157   0.0126
  -6.500  -0.2694   0.01667   0.01210  -0.0852   0.9029   0.0133
  -6.250  -0.2429   0.01675   0.01213  -0.0848   0.8879   0.0142
  -6.000  -0.2176   0.01564   0.01071  -0.0844   0.8710   0.0158
  -5.750  -0.1921   0.01470   0.00946  -0.0840   0.8516   0.0170
  -5.500  -0.1655   0.01486   0.00954  -0.0836   0.8288   0.0178
  -5.250  -0.1389   0.01510   0.00969  -0.0832   0.8042   0.0187
  -5.000  -0.1122   0.01501   0.00942  -0.0829   0.7802   0.0202
  -4.750  -0.0853   0.01458   0.00875  -0.0827   0.7594   0.0218
  -4.500  -0.0579   0.01438   0.00834  -0.0825   0.7410   0.0231
  -4.250  -0.0302   0.01442   0.00822  -0.0824   0.7250   0.0238
  -4.000  -0.0036   0.01306   0.00659  -0.0824   0.7111   0.0254
  -3.750   0.0239   0.01277   0.00620  -0.0824   0.6980   0.0267
  -3.500   0.0516   0.01247   0.00578  -0.0823   0.6859   0.0278
  -3.000   0.1073   0.01177   0.00483  -0.0823   0.6644   0.0300
  -2.750   0.1353   0.01145   0.00442  -0.0822   0.6552   0.0311
  -2.500   0.1632   0.01114   0.00399  -0.0822   0.6462   0.0318
  -2.250   0.1913   0.01085   0.00362  -0.0822   0.6377   0.0323
  -2.000   0.2192   0.01062   0.00330  -0.0821   0.6282   0.0327
  -1.750   0.2471   0.01041   0.00301  -0.0821   0.6163   0.0331
  -1.500   0.2751   0.01023   0.00275  -0.0821   0.6042   0.0334
  -1.250   0.3032   0.01010   0.00256  -0.0821   0.5943   0.0338
  -1.000   0.3313   0.00999   0.00239  -0.0821   0.5858   0.0342
  -0.750   0.3595   0.00984   0.00220  -0.0821   0.5766   0.0343
  -0.500   0.3877   0.00970   0.00200  -0.0822   0.5672   0.0348
  -0.250   0.4158   0.00960   0.00182  -0.0822   0.5574   0.0357
   0.000   0.4441   0.00952   0.00169  -0.0822   0.5480   0.0377
   0.250   0.4722   0.00948   0.00160  -0.0822   0.5377   0.0413
   0.500   0.5002   0.00947   0.00155  -0.0822   0.5254   0.0467
   0.750   0.5280   0.00935   0.00156  -0.0823   0.5112   0.1090
   1.000   0.5557   0.00936   0.00159  -0.0823   0.4948   0.1402
   1.500   0.6110   0.00926   0.00170  -0.0825   0.4679   0.2602
   2.000   0.6629   0.00779   0.00189  -0.0820   0.4441   1.0000
   2.250   0.6905   0.00794   0.00196  -0.0820   0.4319   1.0000
   2.500   0.7179   0.00810   0.00205  -0.0819   0.4200   1.0000
   2.750   0.7453   0.00827   0.00215  -0.0819   0.4087   1.0000
   3.000   0.7727   0.00844   0.00225  -0.0818   0.3968   1.0000
   3.250   0.8000   0.00860   0.00238  -0.0818   0.3860   1.0000
   3.500   0.8273   0.00877   0.00250  -0.0818   0.3766   1.0000
   4.000   0.8817   0.00913   0.00280  -0.0817   0.3559   1.0000
   4.250   0.9085   0.00934   0.00296  -0.0816   0.3421   1.0000
   4.500   0.9348   0.00962   0.00315  -0.0814   0.3234   1.0000
   4.750   0.9611   0.00990   0.00335  -0.0813   0.3063   1.0000
   5.000   0.9868   0.01023   0.00360  -0.0811   0.2805   1.0000
   5.250   1.0112   0.01074   0.00390  -0.0807   0.2396   1.0000
   5.500   1.0340   0.01145   0.00434  -0.0802   0.1899   1.0000
   5.750   1.0584   0.01193   0.00473  -0.0799   0.1720   1.0000
   6.000   1.0834   0.01232   0.00508  -0.0796   0.1604   1.0000
   6.250   1.1083   0.01270   0.00543  -0.0793   0.1503   1.0000
   6.500   1.1329   0.01310   0.00579  -0.0789   0.1360   1.0000
   6.750   1.1515   0.01422   0.00652  -0.0779   0.0702   1.0000
   7.000   1.1686   0.01549   0.00749  -0.0766   0.0186   1.0000
   7.250   1.1915   0.01602   0.00806  -0.0760   0.0145   1.0000
   7.500   1.2139   0.01660   0.00871  -0.0752   0.0115   1.0000
   7.750   1.2368   0.01708   0.00926  -0.0746   0.0107   1.0000
   8.000   1.2589   0.01762   0.00990  -0.0738   0.0099   1.0000
   8.250   1.2800   0.01822   0.01059  -0.0730   0.0090   1.0000
   8.500   1.2997   0.01894   0.01138  -0.0720   0.0082   1.0000
   8.750   1.3174   0.01982   0.01235  -0.0706   0.0075   1.0000
   9.000   1.3363   0.02053   0.01314  -0.0695   0.0071   1.0000
   9.250   1.3534   0.02134   0.01403  -0.0682   0.0067   1.0000
   9.500   1.3690   0.02221   0.01499  -0.0666   0.0064   1.0000
   9.750   1.3828   0.02315   0.01604  -0.0649   0.0061   1.0000
  10.000   1.3930   0.02412   0.01709  -0.0626   0.0058   1.0000
  10.250   1.4010   0.02521   0.01826  -0.0601   0.0056   1.0000
  10.500   1.4065   0.02655   0.01968  -0.0576   0.0054   1.0000
  10.750   1.4050   0.02851   0.02176  -0.0548   0.0052   1.0000
  11.000   1.4117   0.02998   0.02333  -0.0531   0.0050   1.0000
  11.250   1.4180   0.03158   0.02504  -0.0516   0.0048   1.0000
  11.500   1.4225   0.03345   0.02702  -0.0503   0.0046   1.0000
  11.750   1.4245   0.03570   0.02939  -0.0492   0.0045   1.0000
  12.000   1.4256   0.03819   0.03201  -0.0484   0.0044   1.0000
  12.250   1.4260   0.04090   0.03484  -0.0479   0.0043   1.0000
  12.500   1.4257   0.04377   0.03785  -0.0475   0.0042   1.0000
  12.750   1.4245   0.04686   0.04105  -0.0473   0.0041   1.0000
  13.000   1.4229   0.05006   0.04437  -0.0473   0.0040   1.0000
  13.250   1.4205   0.05340   0.04782  -0.0474   0.0039   1.0000
  13.500   1.4173   0.05690   0.05144  -0.0476   0.0038   1.0000
  13.750   1.4135   0.06053   0.05518  -0.0479   0.0038   1.0000
  14.000   1.4090   0.06432   0.05907  -0.0484   0.0037   1.0000
  14.250   1.4040   0.06829   0.06315  -0.0490   0.0037   1.0000
  14.500   1.3983   0.07244   0.06740  -0.0498   0.0036   1.0000
  14.750   1.3922   0.07674   0.07182  -0.0507   0.0036   1.0000
  15.000   1.3855   0.08125   0.07643  -0.0517   0.0035   1.0000
  15.250   1.3783   0.08589   0.08118  -0.0528   0.0035   1.0000
  15.500   1.3702   0.09071   0.08611  -0.0540   0.0034   1.0000
  15.750   1.3612   0.09571   0.09123  -0.0553   0.0034   1.0000
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