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GOE 117 (MVA MK.4) AIRFOIL (goe117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 117 (MVA MK.4) AIRFOIL (goe117-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.88 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe117-il-1000000-n5.txt
Download as CSV file: xf-goe117-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3732   0.11609   0.11444  -0.0332   1.0000   0.0035
 -11.000  -0.3726   0.11195   0.11032  -0.0343   1.0000   0.0036
 -10.500  -0.6148   0.02608   0.02366  -0.1071   0.9501   0.0034
 -10.250  -0.5832   0.02240   0.01954  -0.1123   0.9302   0.0035
 -10.000  -0.5592   0.02043   0.01724  -0.1137   0.9102   0.0036
  -9.750  -0.5386   0.01898   0.01552  -0.1137   0.8953   0.0038
  -9.250  -0.4959   0.01680   0.01288  -0.1129   0.8716   0.0041
  -9.000  -0.4731   0.01599   0.01188  -0.1126   0.8617   0.0042
  -8.750  -0.4522   0.01475   0.01037  -0.1120   0.8514   0.0044
  -8.500  -0.4289   0.01394   0.00940  -0.1116   0.8425   0.0047
  -8.250  -0.4046   0.01332   0.00864  -0.1112   0.8352   0.0050
  -8.000  -0.3798   0.01278   0.00798  -0.1109   0.8278   0.0052
  -7.750  -0.3547   0.01226   0.00731  -0.1106   0.8213   0.0056
  -7.500  -0.3294   0.01179   0.00671  -0.1103   0.8140   0.0059
  -7.250  -0.3037   0.01137   0.00616  -0.1100   0.8071   0.0062
  -7.000  -0.2782   0.01090   0.00557  -0.1097   0.7989   0.0067
  -6.750  -0.2525   0.01048   0.00505  -0.1094   0.7903   0.0076
  -6.500  -0.2266   0.01018   0.00466  -0.1092   0.7806   0.0085
  -6.250  -0.2005   0.00990   0.00427  -0.1089   0.7694   0.0092
  -6.000  -0.1744   0.00960   0.00388  -0.1086   0.7569   0.0109
  -5.750  -0.1482   0.00942   0.00366  -0.1083   0.7414   0.0129
  -5.500  -0.1223   0.00928   0.00344  -0.1080   0.7207   0.0150
  -5.250  -0.0966   0.00932   0.00342  -0.1075   0.6912   0.0182
  -5.000  -0.0709   0.00939   0.00336  -0.1071   0.6624   0.0205
  -4.750  -0.0449   0.00943   0.00327  -0.1068   0.6404   0.0218
  -4.500  -0.0184   0.00948   0.00323  -0.1065   0.6242   0.0225
  -4.250   0.0086   0.00954   0.00323  -0.1064   0.6116   0.0229
  -4.000   0.0349   0.00928   0.00286  -0.1062   0.6019   0.0238
  -3.750   0.0612   0.00902   0.00249  -0.1059   0.5939   0.0252
  -3.500   0.0881   0.00885   0.00225  -0.1058   0.5868   0.0261
  -3.250   0.1150   0.00872   0.00206  -0.1056   0.5804   0.0269
  -3.000   0.1422   0.00859   0.00188  -0.1055   0.5746   0.0276
  -2.750   0.1693   0.00849   0.00170  -0.1053   0.5686   0.0280
  -2.500   0.1964   0.00839   0.00155  -0.1052   0.5634   0.0284
  -2.250   0.2237   0.00830   0.00142  -0.1051   0.5583   0.0293
  -2.000   0.2509   0.00824   0.00131  -0.1050   0.5536   0.0307
  -1.750   0.2782   0.00818   0.00122  -0.1049   0.5498   0.0325
  -1.500   0.3057   0.00813   0.00115  -0.1048   0.5458   0.0341
  -1.250   0.3330   0.00808   0.00109  -0.1047   0.5416   0.0411
  -0.750   0.3864   0.00775   0.00101  -0.1045   0.5343   0.1318
  -0.500   0.4139   0.00773   0.00100  -0.1044   0.5308   0.1415
  -0.250   0.4411   0.00771   0.00100  -0.1043   0.5271   0.1494
   0.000   0.4683   0.00772   0.00100  -0.1042   0.5236   0.1555
   0.250   0.4956   0.00770   0.00101  -0.1042   0.5200   0.1653
   0.500   0.5228   0.00766   0.00102  -0.1041   0.5151   0.1820
   0.750   0.5494   0.00759   0.00107  -0.1040   0.5103   0.2275
   1.000   0.5764   0.00757   0.00114  -0.1039   0.5066   0.2609
   1.250   0.6037   0.00757   0.00118  -0.1038   0.5035   0.2772
   1.500   0.6311   0.00759   0.00123  -0.1038   0.5002   0.2847
   1.750   0.6581   0.00762   0.00128  -0.1037   0.4962   0.2933
   2.000   0.6851   0.00766   0.00134  -0.1035   0.4898   0.3006
   2.250   0.7120   0.00770   0.00139  -0.1034   0.4825   0.3091
   2.500   0.7389   0.00773   0.00147  -0.1033   0.4780   0.3213
   2.750   0.7656   0.00776   0.00154  -0.1031   0.4688   0.3357
   3.000   0.7920   0.00779   0.00163  -0.1030   0.4595   0.3594
   3.250   0.8167   0.00762   0.00178  -0.1026   0.4461   0.5102
   3.750   0.8719   0.00746   0.00227  -0.1033   0.3472   1.0000
   4.000   0.8896   0.00825   0.00269  -0.1016   0.2728   1.0000
   4.250   0.8959   0.01004   0.00365  -0.0981   0.0865   1.0000
   4.500   0.9174   0.01052   0.00397  -0.0971   0.0473   1.0000
   4.750   0.9410   0.01082   0.00422  -0.0964   0.0355   1.0000
   5.000   0.9647   0.01110   0.00447  -0.0957   0.0294   1.0000
   5.250   0.9887   0.01135   0.00474  -0.0951   0.0245   1.0000
   5.500   1.0117   0.01168   0.00503  -0.0944   0.0162   1.0000
   5.750   1.0348   0.01199   0.00532  -0.0936   0.0132   1.0000
   6.000   1.0571   0.01236   0.00569  -0.0927   0.0101   1.0000
   6.250   1.0799   0.01266   0.00602  -0.0919   0.0092   1.0000
   6.500   1.1021   0.01300   0.00640  -0.0910   0.0081   1.0000
   6.750   1.1230   0.01343   0.00683  -0.0899   0.0071   1.0000
   7.000   1.1433   0.01388   0.00733  -0.0887   0.0064   1.0000
   7.250   1.1638   0.01428   0.00777  -0.0875   0.0060   1.0000
   7.500   1.1834   0.01473   0.00827  -0.0862   0.0056   1.0000
   7.750   1.2025   0.01518   0.00874  -0.0849   0.0052   1.0000
   8.000   1.2205   0.01567   0.00926  -0.0833   0.0048   1.0000
   8.250   1.2353   0.01630   0.00995  -0.0813   0.0043   1.0000
   8.500   1.2492   0.01684   0.01055  -0.0790   0.0041   1.0000
   8.750   1.2612   0.01742   0.01119  -0.0763   0.0040   1.0000
   9.000   1.2725   0.01805   0.01188  -0.0737   0.0038   1.0000
   9.250   1.2837   0.01871   0.01261  -0.0711   0.0037   1.0000
   9.500   1.2934   0.01947   0.01344  -0.0685   0.0035   1.0000
   9.750   1.3036   0.02026   0.01428  -0.0661   0.0034   1.0000
  10.000   1.3122   0.02117   0.01526  -0.0636   0.0033   1.0000
  10.250   1.3213   0.02210   0.01626  -0.0614   0.0032   1.0000
  10.500   1.3292   0.02317   0.01740  -0.0592   0.0031   1.0000
  10.750   1.3384   0.02422   0.01850  -0.0573   0.0029   1.0000
  11.000   1.3447   0.02554   0.01989  -0.0552   0.0028   1.0000
  11.250   1.3475   0.02721   0.02168  -0.0529   0.0027   1.0000
  11.500   1.3484   0.02915   0.02374  -0.0507   0.0026   1.0000
  11.750   1.3567   0.03053   0.02521  -0.0492   0.0026   1.0000
  12.000   1.3623   0.03221   0.02700  -0.0477   0.0026   1.0000
  12.250   1.3679   0.03396   0.02885  -0.0462   0.0025   1.0000
  12.500   1.3761   0.03547   0.03046  -0.0452   0.0024   1.0000
  12.750   1.3794   0.03758   0.03270  -0.0438   0.0024   1.0000
  13.000   1.3867   0.03927   0.03448  -0.0429   0.0023   1.0000
  13.250   1.3900   0.04147   0.03680  -0.0419   0.0022   1.0000
  13.500   1.3950   0.04354   0.03898  -0.0411   0.0021   1.0000
  13.750   1.3992   0.04571   0.04126  -0.0404   0.0021   1.0000
  14.000   1.3995   0.04846   0.04416  -0.0396   0.0020   1.0000
  14.250   1.4027   0.05090   0.04671  -0.0392   0.0020   1.0000
  14.500   1.4020   0.05388   0.04984  -0.0388   0.0020   1.0000
  14.750   1.4009   0.05702   0.05315  -0.0386   0.0020   1.0000
  15.000   1.4005   0.06015   0.05641  -0.0387   0.0019   1.0000
  15.250   1.3966   0.06387   0.06028  -0.0389   0.0019   1.0000
  15.500   1.3979   0.06688   0.06338  -0.0393   0.0018   1.0000
  15.750   1.3892   0.07151   0.06820  -0.0400   0.0018   1.0000
  16.000   1.3832   0.07588   0.07271  -0.0409   0.0018   1.0000
  16.250   1.3783   0.08013   0.07710  -0.0420   0.0018   1.0000
  16.500   1.3623   0.08643   0.08360  -0.0438   0.0018   1.0000
  16.750   1.3513   0.09209   0.08942  -0.0458   0.0017   1.0000
  17.000   1.3386   0.09826   0.09576  -0.0482   0.0017   1.0000
  17.250   1.3233   0.10516   0.10281  -0.0512   0.0017   1.0000
  17.500   1.3057   0.11286   0.11069  -0.0548   0.0017   1.0000
  17.750   1.2591   0.12751   0.12567  -0.0624   0.0018   1.0000
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