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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 200,000
Max Cl/Cd: 77.76 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe117-il-200000-n5.txt
Download as CSV file: xf-goe117-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 117 (MVA MK.4) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3391   0.09887   0.09540  -0.0411   1.0000   0.0138
  -9.250  -0.3390   0.09569   0.09227  -0.0415   1.0000   0.0137
  -9.000  -0.3408   0.09201   0.08864  -0.0425   1.0000   0.0142
  -8.000  -0.3398   0.07607   0.07292  -0.0508   0.9845   0.0142
  -7.750  -0.3314   0.06931   0.06620  -0.0587   0.9693   0.0143
  -7.250  -0.3011   0.04757   0.04427  -0.0859   0.9428   0.0143
  -7.000  -0.2828   0.03163   0.02735  -0.1019   0.9298   0.0144
  -6.750  -0.2567   0.02817   0.02349  -0.1051   0.9221   0.0154
  -6.500  -0.2276   0.02700   0.02212  -0.1068   0.9144   0.0169
  -6.250  -0.2006   0.02436   0.01894  -0.1082   0.9066   0.0187
  -6.000  -0.1736   0.02164   0.01561  -0.1091   0.8986   0.0205
  -5.750  -0.1457   0.02023   0.01374  -0.1094   0.8899   0.0225
  -5.500  -0.1182   0.01852   0.01176  -0.1100   0.8818   0.0253
  -5.250  -0.0919   0.01757   0.01061  -0.1099   0.8720   0.0279
  -5.000  -0.0646   0.01684   0.00963  -0.1099   0.8627   0.0315
  -4.750  -0.0364   0.01625   0.00876  -0.1099   0.8537   0.0338
  -4.500  -0.0117   0.01509   0.00748  -0.1095   0.8435   0.0369
  -4.250   0.0145   0.01453   0.00683  -0.1093   0.8334   0.0400
  -4.000   0.0409   0.01400   0.00616  -0.1090   0.8229   0.0417
  -3.750   0.0673   0.01361   0.00560  -0.1086   0.8115   0.0441
  -3.500   0.0933   0.01324   0.00510  -0.1082   0.7990   0.0454
  -3.250   0.1193   0.01289   0.00462  -0.1077   0.7859   0.0463
  -3.000   0.1454   0.01252   0.00411  -0.1073   0.7723   0.0487
  -2.750   0.1716   0.01223   0.00370  -0.1069   0.7578   0.0528
  -2.500   0.1978   0.01198   0.00335  -0.1065   0.7423   0.0604
  -2.250   0.2230   0.01152   0.00309  -0.1061   0.7259   0.1259
  -2.000   0.2490   0.01141   0.00291  -0.1057   0.7089   0.1592
  -1.750   0.2749   0.01132   0.00276  -0.1053   0.6925   0.1801
  -1.500   0.3007   0.01124   0.00270  -0.1049   0.6783   0.2079
  -1.250   0.3267   0.01124   0.00267  -0.1045   0.6662   0.2374
  -1.000   0.3529   0.01125   0.00264  -0.1042   0.6554   0.2609
  -0.750   0.3792   0.01127   0.00262  -0.1039   0.6456   0.2846
  -0.500   0.4053   0.01128   0.00259  -0.1036   0.6371   0.3056
  -0.250   0.4316   0.01128   0.00257  -0.1033   0.6292   0.3207
   0.000   0.4580   0.01129   0.00256  -0.1031   0.6228   0.3359
   0.500   0.5104   0.01128   0.00261  -0.1025   0.6105   0.3789
   0.750   0.5360   0.01118   0.00268  -0.1022   0.6046   0.4305
   1.000   0.5585   0.01070   0.00278  -0.1013   0.5995   0.6200
   1.250   0.6073   0.01020   0.00286  -0.1054   0.5944   1.0000
   1.500   0.6333   0.01033   0.00296  -0.1051   0.5890   1.0000
   1.750   0.6593   0.01048   0.00307  -0.1047   0.5841   1.0000
   2.000   0.6854   0.01065   0.00319  -0.1044   0.5793   1.0000
   2.250   0.7113   0.01079   0.00333  -0.1041   0.5737   1.0000
   2.500   0.7372   0.01096   0.00349  -0.1037   0.5685   1.0000
   2.750   0.7632   0.01112   0.00366  -0.1034   0.5636   1.0000
   3.000   0.7891   0.01127   0.00385  -0.1031   0.5585   1.0000
   3.250   0.8152   0.01145   0.00406  -0.1028   0.5541   1.0000
   3.500   0.8411   0.01163   0.00428  -0.1024   0.5495   1.0000
   3.750   0.8656   0.01177   0.00445  -0.1018   0.5391   1.0000
   4.000   0.8890   0.01190   0.00458  -0.1009   0.5243   1.0000
   4.250   0.9128   0.01203   0.00478  -0.1000   0.5106   1.0000
   4.500   0.9362   0.01218   0.00497  -0.0991   0.4953   1.0000
   4.750   0.9588   0.01233   0.00517  -0.0981   0.4741   1.0000
   5.000   0.9778   0.01258   0.00531  -0.0964   0.4254   1.0000
   5.250   0.9833   0.01382   0.00582  -0.0926   0.2941   1.0000
   5.500   0.9759   0.01654   0.00741  -0.0875   0.0802   1.0000
   5.750   0.9913   0.01746   0.00820  -0.0856   0.0492   1.0000
   6.000   1.0080   0.01822   0.00899  -0.0838   0.0374   1.0000
   6.250   1.0248   0.01893   0.00980  -0.0821   0.0305   1.0000
   6.500   1.0382   0.01981   0.01075  -0.0798   0.0256   1.0000
   6.750   1.0510   0.02067   0.01175  -0.0775   0.0228   1.0000
   7.000   1.0616   0.02156   0.01277  -0.0748   0.0202   1.0000
   7.250   1.0694   0.02252   0.01378  -0.0717   0.0180   1.0000
   7.500   1.0674   0.02413   0.01545  -0.0674   0.0164   1.0000
   7.750   1.0747   0.02529   0.01672  -0.0646   0.0158   1.0000
   8.000   1.0812   0.02663   0.01817  -0.0618   0.0151   1.0000
   8.250   1.0885   0.02809   0.01973  -0.0593   0.0145   1.0000
   8.500   1.0986   0.02947   0.02120  -0.0572   0.0135   1.0000
   8.750   1.1102   0.03078   0.02259  -0.0555   0.0125   1.0000
   9.000   1.1220   0.03202   0.02391  -0.0539   0.0116   1.0000
   9.250   1.1346   0.03356   0.02552  -0.0524   0.0110   1.0000
   9.500   1.1505   0.03551   0.02761  -0.0510   0.0105   1.0000
   9.750   1.1794   0.03869   0.03100  -0.0507   0.0100   1.0000
  10.000   1.2000   0.04110   0.03369  -0.0498   0.0097   1.0000
  10.250   1.2161   0.04370   0.03659  -0.0486   0.0094   1.0000
  10.500   1.2270   0.04630   0.03950  -0.0469   0.0090   1.0000
  10.750   1.2332   0.04881   0.04229  -0.0449   0.0083   1.0000
  11.000   1.2357   0.05177   0.04553  -0.0429   0.0080   1.0000
  11.250   1.2337   0.05518   0.04923  -0.0408   0.0079   1.0000
  11.500   1.2279   0.05886   0.05319  -0.0388   0.0078   1.0000
  11.750   1.2187   0.06276   0.05735  -0.0370   0.0078   1.0000
  12.000   1.2064   0.06709   0.06195  -0.0356   0.0078   1.0000
  12.250   1.1925   0.07151   0.06661  -0.0348   0.0078   1.0000
  12.500   1.1762   0.07641   0.07174  -0.0346   0.0078   1.0000
  12.750   1.1587   0.08165   0.07719  -0.0351   0.0078   1.0000
  13.000   1.1399   0.08739   0.08314  -0.0363   0.0078   1.0000
  13.250   1.1205   0.09350   0.08943  -0.0383   0.0079   1.0000
  13.500   1.1006   0.10008   0.09619  -0.0410   0.0080   1.0000
  13.750   1.0800   0.10731   0.10358  -0.0444   0.0080   1.0000
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