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GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.99 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe133-il-1000000-n5.txt
Download as CSV file: xf-goe133-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 133 (MVA H.11) 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3778   0.09256   0.09097  -0.0212   1.0000   0.0048
  -8.250  -0.4432   0.01878   0.01538  -0.0899   0.9614   0.0054
  -8.000  -0.4192   0.01668   0.01303  -0.0901   0.9547   0.0056
  -7.750  -0.3940   0.01535   0.01149  -0.0901   0.9483   0.0058
  -7.500  -0.3685   0.01437   0.01034  -0.0899   0.9408   0.0060
  -7.250  -0.3427   0.01350   0.00931  -0.0897   0.9332   0.0061
  -7.000  -0.3168   0.01279   0.00844  -0.0893   0.9238   0.0064
  -6.750  -0.2903   0.01212   0.00763  -0.0891   0.9150   0.0067
  -6.500  -0.2637   0.01154   0.00691  -0.0888   0.9069   0.0069
  -6.250  -0.2365   0.01104   0.00627  -0.0887   0.8975   0.0071
  -6.000  -0.2096   0.01056   0.00566  -0.0884   0.8868   0.0074
  -5.750  -0.1827   0.01005   0.00503  -0.0882   0.8746   0.0080
  -5.500  -0.1555   0.00971   0.00460  -0.0879   0.8612   0.0086
  -5.250  -0.1282   0.00942   0.00421  -0.0877   0.8464   0.0092
  -5.000  -0.1009   0.00916   0.00382  -0.0874   0.8288   0.0098
  -4.750  -0.0736   0.00893   0.00346  -0.0871   0.8076   0.0103
  -4.500  -0.0464   0.00867   0.00307  -0.0869   0.7854   0.0115
  -4.250  -0.0190   0.00850   0.00279  -0.0867   0.7641   0.0128
  -4.000   0.0087   0.00837   0.00253  -0.0865   0.7453   0.0142
  -3.750   0.0364   0.00821   0.00231  -0.0864   0.7278   0.0173
  -3.500   0.0642   0.00811   0.00216  -0.0863   0.7101   0.0210
  -3.250   0.0921   0.00807   0.00204  -0.0862   0.6915   0.0247
  -3.000   0.1198   0.00806   0.00196  -0.0860   0.6681   0.0278
  -2.750   0.1474   0.00811   0.00191  -0.0859   0.6394   0.0306
  -2.500   0.1749   0.00818   0.00183  -0.0857   0.6053   0.0321
  -2.250   0.2024   0.00821   0.00172  -0.0856   0.5728   0.0341
  -1.750   0.2579   0.00830   0.00164  -0.0854   0.5282   0.0387
  -1.500   0.2858   0.00834   0.00159  -0.0854   0.5092   0.0403
  -1.250   0.3137   0.00836   0.00153  -0.0853   0.4936   0.0413
  -1.000   0.3417   0.00837   0.00147  -0.0853   0.4803   0.0418
  -0.750   0.3698   0.00831   0.00134  -0.0853   0.4691   0.0442
  -0.250   0.4261   0.00829   0.00125  -0.0852   0.4486   0.0490
   0.000   0.4542   0.00831   0.00123  -0.0852   0.4387   0.0511
   0.250   0.4821   0.00835   0.00122  -0.0852   0.4278   0.0530
   0.500   0.5102   0.00837   0.00120  -0.0852   0.4176   0.0565
   0.750   0.5383   0.00838   0.00121  -0.0852   0.4097   0.0631
   1.250   0.5944   0.00836   0.00127  -0.0852   0.3945   0.1113
   1.500   0.6223   0.00835   0.00132  -0.0852   0.3858   0.1476
   1.750   0.6486   0.00715   0.00152  -0.0857   0.3777   0.7295
   2.000   0.6731   0.00667   0.00158  -0.0847   0.3676   1.0000
   2.250   0.7007   0.00681   0.00164  -0.0846   0.3530   1.0000
   2.500   0.7278   0.00703   0.00173  -0.0845   0.3263   1.0000
   2.750   0.7539   0.00739   0.00187  -0.0843   0.2842   1.0000
   3.000   0.7796   0.00781   0.00207  -0.0840   0.2433   1.0000
   3.250   0.8063   0.00808   0.00223  -0.0839   0.2235   1.0000
   3.500   0.8334   0.00829   0.00237  -0.0838   0.2114   1.0000
   3.750   0.8605   0.00848   0.00251  -0.0837   0.2027   1.0000
   4.000   0.8874   0.00870   0.00267  -0.0835   0.1928   1.0000
   4.250   0.9145   0.00887   0.00281  -0.0834   0.1855   1.0000
   4.500   0.9413   0.00909   0.00298  -0.0833   0.1767   1.0000
   4.750   0.9683   0.00928   0.00314  -0.0832   0.1704   1.0000
   5.000   0.9952   0.00947   0.00331  -0.0831   0.1654   1.0000
   5.250   1.0222   0.00964   0.00348  -0.0830   0.1617   1.0000
   5.500   1.0491   0.00981   0.00366  -0.0829   0.1576   1.0000
   5.750   1.0756   0.01002   0.00385  -0.0827   0.1522   1.0000
   6.000   1.1022   0.01022   0.00404  -0.0826   0.1470   1.0000
   6.250   1.1285   0.01045   0.00425  -0.0824   0.1385   1.0000
   6.500   1.1523   0.01099   0.00460  -0.0819   0.1024   1.0000
   6.750   1.1760   0.01154   0.00504  -0.0814   0.0814   1.0000
   7.000   1.2010   0.01191   0.00539  -0.0811   0.0739   1.0000
   7.250   1.2265   0.01219   0.00570  -0.0808   0.0696   1.0000
   7.500   1.2506   0.01264   0.00611  -0.0803   0.0605   1.0000
   7.750   1.2756   0.01295   0.00642  -0.0800   0.0561   1.0000
   8.000   1.2996   0.01337   0.00681  -0.0795   0.0496   1.0000
   8.250   1.3242   0.01370   0.00716  -0.0791   0.0457   1.0000
   8.500   1.3479   0.01412   0.00756  -0.0786   0.0412   1.0000
   8.750   1.3718   0.01450   0.00795  -0.0782   0.0377   1.0000
   9.000   1.3952   0.01492   0.00837  -0.0776   0.0335   1.0000
   9.250   1.4179   0.01539   0.00883  -0.0770   0.0287   1.0000
   9.750   1.4580   0.01682   0.01018  -0.0751   0.0115   1.0000
  10.000   1.4784   0.01746   0.01084  -0.0741   0.0093   1.0000
  10.250   1.4990   0.01803   0.01146  -0.0732   0.0079   1.0000
  10.500   1.5184   0.01868   0.01215  -0.0722   0.0068   1.0000
  10.750   1.5374   0.01933   0.01284  -0.0711   0.0060   1.0000
  11.000   1.5563   0.01994   0.01351  -0.0699   0.0055   1.0000
  11.250   1.5738   0.02063   0.01426  -0.0686   0.0051   1.0000
  11.500   1.5896   0.02141   0.01510  -0.0671   0.0046   1.0000
  11.750   1.6041   0.02221   0.01597  -0.0654   0.0043   1.0000
  12.000   1.6164   0.02294   0.01678  -0.0633   0.0041   1.0000
  12.250   1.6272   0.02377   0.01769  -0.0610   0.0039   1.0000
  12.500   1.6369   0.02469   0.01869  -0.0588   0.0037   1.0000
  12.750   1.6456   0.02572   0.01979  -0.0567   0.0036   1.0000
  13.000   1.6530   0.02689   0.02103  -0.0545   0.0034   1.0000
  13.250   1.6586   0.02825   0.02249  -0.0525   0.0032   1.0000
  13.500   1.6615   0.02993   0.02427  -0.0504   0.0030   1.0000
  13.750   1.6665   0.03153   0.02597  -0.0488   0.0029   1.0000
  14.000   1.6706   0.03331   0.02785  -0.0475   0.0028   1.0000
  14.250   1.6734   0.03533   0.02998  -0.0463   0.0028   1.0000
  14.500   1.6749   0.03763   0.03238  -0.0454   0.0027   1.0000
  14.750   1.6747   0.04025   0.03512  -0.0448   0.0026   1.0000
  15.000   1.6731   0.04321   0.03819  -0.0446   0.0025   1.0000
  15.250   1.6704   0.04646   0.04156  -0.0447   0.0025   1.0000
  15.500   1.6652   0.05016   0.04538  -0.0451   0.0024   1.0000
  15.750   1.6589   0.05420   0.04954  -0.0458   0.0024   1.0000
  16.000   1.6505   0.05866   0.05413  -0.0468   0.0023   1.0000
  16.250   1.6400   0.06357   0.05917  -0.0481   0.0023   1.0000
  16.500   1.6277   0.06892   0.06464  -0.0497   0.0023   1.0000
  16.750   1.6134   0.07462   0.07049  -0.0515   0.0023   1.0000
  17.000   1.5973   0.08069   0.07669  -0.0536   0.0022   1.0000
  17.250   1.5801   0.08710   0.08323  -0.0558   0.0022   1.0000
  17.500   1.5615   0.09380   0.09006  -0.0582   0.0022   1.0000
  17.750   1.5420   0.10084   0.09723  -0.0609   0.0022   1.0000
  18.000   1.5219   0.10818   0.10469  -0.0639   0.0022   1.0000
  18.250   1.5019   0.11562   0.11226  -0.0670   0.0022   1.0000
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