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GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il)
Reynolds number: 100,000
Max Cl/Cd: 56.87 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe137-il-100000.txt
Download as CSV file: xf-goe137-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3443   0.09760   0.09295  -0.0228   1.0000   0.0765
  -7.750  -0.3523   0.09631   0.09178  -0.0272   1.0000   0.0785
  -7.500  -0.3546   0.09472   0.09026  -0.0373   1.0000   0.0792
  -7.250  -0.3412   0.08864   0.08423  -0.0276   1.0000   0.0819
  -7.000  -0.3345   0.08574   0.08135  -0.0269   1.0000   0.0850
  -6.750  -0.3325   0.08317   0.07885  -0.0283   1.0000   0.0886
  -6.500  -0.3345   0.08184   0.07753  -0.0378   1.0000   0.0924
  -6.250  -0.3340   0.07794   0.07370  -0.0377   1.0000   0.0936
  -6.000  -0.3323   0.07488   0.07074  -0.0320   1.0000   0.0957
  -5.750  -0.3317   0.07270   0.06862  -0.0299   1.0000   0.0987
  -5.500  -0.3318   0.07065   0.06661  -0.0301   1.0000   0.1029
  -5.250  -0.3265   0.06828   0.06408  -0.0369   1.0000   0.1077
  -5.000  -0.3309   0.06580   0.06176  -0.0321   1.0000   0.1096
  -4.750  -0.2909   0.06173   0.05744  -0.0417   0.9944   0.1227
  -4.500  -0.2606   0.05769   0.05346  -0.0435   0.9872   0.1302
  -4.250  -0.2155   0.05308   0.04864  -0.0515   0.9791   0.1425
  -4.000  -0.1694   0.04898   0.04435  -0.0587   0.9715   0.1586
  -3.750  -0.1243   0.04538   0.04046  -0.0657   0.9617   0.1825
  -3.500  -0.0793   0.04170   0.03667  -0.0708   0.9559   0.2003
  -3.250  -0.0397   0.03887   0.03365  -0.0750   0.9454   0.2280
  -2.750   0.0831   0.02709   0.01963  -0.0875   0.9321   0.1019
  -2.500   0.1319   0.02465   0.01668  -0.0911   0.9263   0.1013
  -2.250   0.1697   0.02297   0.01461  -0.0925   0.9150   0.1017
  -2.000   0.2068   0.02154   0.01287  -0.0936   0.9041   0.1022
  -1.750   0.2442   0.02034   0.01144  -0.0946   0.8943   0.1048
  -1.500   0.2781   0.01934   0.01039  -0.0951   0.8837   0.1113
  -1.250   0.3077   0.01871   0.00969  -0.0948   0.8708   0.1203
  -1.000   0.3357   0.01794   0.00902  -0.0942   0.8583   0.1310
  -0.750   0.3632   0.01720   0.00838  -0.0934   0.8461   0.1572
  -0.500   0.3960   0.01410   0.00765  -0.0933   0.8364   1.0000
  -0.250   0.4235   0.01412   0.00731  -0.0924   0.8244   1.0000
   0.000   0.4495   0.01422   0.00716  -0.0915   0.8110   1.0000
   0.250   0.4754   0.01434   0.00706  -0.0907   0.7977   1.0000
   0.500   0.5014   0.01448   0.00702  -0.0899   0.7845   1.0000
   0.750   0.5274   0.01463   0.00701  -0.0891   0.7715   1.0000
   1.000   0.5534   0.01481   0.00703  -0.0884   0.7587   1.0000
   1.250   0.5795   0.01499   0.00707  -0.0876   0.7458   1.0000
   1.500   0.6055   0.01518   0.00712  -0.0868   0.7327   1.0000
   1.750   0.6314   0.01538   0.00718  -0.0861   0.7193   1.0000
   2.000   0.6574   0.01558   0.00727  -0.0853   0.7057   1.0000
   2.250   0.6833   0.01578   0.00736  -0.0845   0.6920   1.0000
   2.500   0.7091   0.01603   0.00752  -0.0838   0.6779   1.0000
   2.750   0.7349   0.01630   0.00773  -0.0832   0.6643   1.0000
   3.000   0.7608   0.01658   0.00799  -0.0827   0.6509   1.0000
   3.250   0.7865   0.01685   0.00821  -0.0821   0.6373   1.0000
   3.500   0.8124   0.01712   0.00845  -0.0815   0.6241   1.0000
   3.750   0.8383   0.01739   0.00872  -0.0810   0.6114   1.0000
   4.000   0.8642   0.01764   0.00894  -0.0804   0.5986   1.0000
   4.250   0.8902   0.01786   0.00913  -0.0798   0.5860   1.0000
   4.500   0.9165   0.01807   0.00930  -0.0792   0.5741   1.0000
   4.750   0.9419   0.01837   0.00968  -0.0787   0.5612   1.0000
   5.000   0.9674   0.01869   0.01006  -0.0783   0.5488   1.0000
   5.250   0.9929   0.01901   0.01044  -0.0778   0.5367   1.0000
   5.500   1.0185   0.01930   0.01078  -0.0772   0.5248   1.0000
   5.750   1.0442   0.01958   0.01111  -0.0767   0.5125   1.0000
   6.000   1.0698   0.01984   0.01141  -0.0761   0.4995   1.0000
   6.250   1.0946   0.02010   0.01173  -0.0754   0.4848   1.0000
   6.500   1.1188   0.02037   0.01208  -0.0745   0.4685   1.0000
   6.750   1.1426   0.02066   0.01248  -0.0737   0.4511   1.0000
   7.000   1.1660   0.02084   0.01265  -0.0726   0.4310   1.0000
   7.250   1.1870   0.02101   0.01285  -0.0713   0.4059   1.0000
   7.500   1.2075   0.02126   0.01308  -0.0699   0.3808   1.0000
   7.750   1.2273   0.02158   0.01340  -0.0685   0.3555   1.0000
   8.000   1.2464   0.02202   0.01394  -0.0672   0.3302   1.0000
   8.250   1.2651   0.02252   0.01451  -0.0658   0.3056   1.0000
   8.500   1.2828   0.02307   0.01512  -0.0644   0.2800   1.0000
   8.750   1.2989   0.02370   0.01582  -0.0628   0.2491   1.0000
   9.000   1.3101   0.02474   0.01670  -0.0608   0.2054   1.0000
   9.250   1.3139   0.02663   0.01827  -0.0581   0.1530   1.0000
   9.500   1.3078   0.02951   0.02049  -0.0545   0.0781   1.0000
   9.750   1.3032   0.03194   0.02286  -0.0507   0.0641   1.0000
  10.000   1.2974   0.03429   0.02523  -0.0472   0.0582   1.0000
  10.250   1.2979   0.03634   0.02744  -0.0447   0.0541   1.0000
  10.500   1.2971   0.03861   0.02981  -0.0425   0.0506   1.0000
  10.750   1.2929   0.04132   0.03256  -0.0407   0.0481   1.0000
  11.000   1.2929   0.04384   0.03520  -0.0391   0.0459   1.0000
  11.250   1.2956   0.04623   0.03772  -0.0377   0.0439   1.0000
  11.500   1.2996   0.04862   0.04023  -0.0363   0.0425   1.0000
  11.750   1.3061   0.05088   0.04256  -0.0347   0.0412   1.0000
  12.000   1.3163   0.05302   0.04474  -0.0330   0.0401   1.0000
  12.250   1.3332   0.05508   0.04682  -0.0311   0.0391   1.0000
  12.500   1.3622   0.05790   0.04969  -0.0292   0.0381   1.0000
  12.750   1.3687   0.06114   0.05318  -0.0280   0.0375   1.0000
  13.000   1.3665   0.06441   0.05677  -0.0270   0.0371   1.0000
  13.250   1.3615   0.06806   0.06072  -0.0263   0.0367   1.0000
  13.500   1.3535   0.07210   0.06508  -0.0260   0.0365   1.0000
  13.750   1.3429   0.07656   0.06983  -0.0261   0.0364   1.0000
  14.000   1.3301   0.08143   0.07497  -0.0266   0.0365   1.0000
  14.250   1.3152   0.08672   0.08052  -0.0277   0.0367   1.0000
  14.500   1.2986   0.09239   0.08642  -0.0294   0.0369   1.0000
  14.750   1.2805   0.09849   0.09275  -0.0316   0.0371   1.0000
  15.000   1.2616   0.10496   0.09942  -0.0344   0.0373   1.0000
  15.250   1.2423   0.11188   0.10653  -0.0378   0.0375   1.0000
  15.500   1.2238   0.11922   0.11403  -0.0415   0.0378   1.0000
  15.750   1.2040   0.12691   0.12190  -0.0466   0.0381   1.0000
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