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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.21 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe388-il-1000000-n5.txt
Download as CSV file: xf-goe388-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 388 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3166   0.10782   0.10321  -0.0377   0.0409   0.0116
 -10.250  -0.3101   0.10479   0.10018  -0.0393   0.0403   0.0121
  -9.750  -0.3182   0.09331   0.08872  -0.0451   0.0408   0.0140
  -9.500  -0.3096   0.09089   0.08631  -0.0466   0.0401   0.0142
  -9.250  -0.3008   0.08848   0.08391  -0.0481   0.0396   0.0143
  -9.000  -0.2919   0.08605   0.08149  -0.0497   0.0394   0.0145
  -8.750  -0.2829   0.08361   0.07905  -0.0513   0.0393   0.0147
  -8.500  -0.2742   0.08102   0.07646  -0.0532   0.0391   0.0150
  -8.250  -0.2670   0.07817   0.07362  -0.0554   0.0387   0.0154
  -8.000  -0.2615   0.07469   0.07016  -0.0589   0.0385   0.0158
  -7.750  -0.2525   0.06927   0.06474  -0.0658   0.0384   0.0165
  -7.500  -0.2449   0.05500   0.05038  -0.0850   0.0391   0.0183
  -7.250  -0.2230   0.05170   0.04701  -0.0895   0.0385   0.0186
  -7.000  -0.2000   0.04753   0.04277  -0.0946   0.0381   0.0188
  -6.750  -0.1760   0.04226   0.03736  -0.1002   0.0377   0.0192
  -6.500  -0.1602   0.02248   0.01634  -0.1115   0.0383   0.0218
  -6.250  -0.1353   0.02048   0.01403  -0.1120   0.0377   0.0222
  -5.750  -0.0830   0.01836   0.01152  -0.1125   0.0371   0.0226
  -5.500  -0.0564   0.01758   0.01058  -0.1127   0.0357   0.0227
  -5.250  -0.0298   0.01697   0.00985  -0.1128   0.0351   0.0228
  -5.000  -0.0028   0.01638   0.00912  -0.1129   0.0350   0.0229
  -4.750   0.0243   0.01585   0.00847  -0.1130   0.0344   0.0230
  -4.500   0.0513   0.01542   0.00793  -0.1131   0.0338   0.0231
  -4.250   0.0784   0.01507   0.00750  -0.1131   0.0334   0.0231
  -4.000   0.1048   0.01402   0.00626  -0.1132   0.0331   0.0238
  -3.750   0.1311   0.01379   0.00596  -0.1132   0.0329   0.0241
  -3.500   0.1581   0.01355   0.00566  -0.1132   0.0329   0.0244
  -3.250   0.1852   0.01338   0.00545  -0.1132   0.0329   0.0247
  -3.000   0.2123   0.01326   0.00530  -0.1132   0.0329   0.0250
  -2.500   0.2668   0.01303   0.00499  -0.1133   0.0321   0.0258
  -1.250   0.3960   0.01365   0.00545  -0.1124   0.0308   0.0277
  -1.000   0.4223   0.01370   0.00547  -0.1124   0.0307   0.0281
  -0.750   0.4484   0.01378   0.00552  -0.1123   0.0307   0.0284
  -0.500   0.4744   0.01389   0.00559  -0.1122   0.0307   0.0287
  -0.250   0.5002   0.01402   0.00570  -0.1120   0.0307   0.0290
   0.000   0.5257   0.01419   0.00584  -0.1119   0.0306   0.0292
   0.250   0.5510   0.01439   0.00601  -0.1117   0.0306   0.0296
   0.500   0.5761   0.01460   0.00620  -0.1115   0.0305   0.0301
   0.750   0.6012   0.01481   0.00637  -0.1112   0.0305   0.0316
   1.000   0.6259   0.01507   0.00660  -0.1110   0.0304   0.0334
   1.250   0.6506   0.01535   0.00687  -0.1107   0.0303   0.0353
   1.500   0.6751   0.01564   0.00715  -0.1104   0.0301   0.0374
   1.750   0.6995   0.01597   0.00746  -0.1101   0.0299   0.0420
   2.000   0.7236   0.01632   0.00782  -0.1098   0.0298   0.0540
   2.250   0.7479   0.01657   0.00822  -0.1096   0.0298   0.1318
   2.500   0.7721   0.01694   0.00862  -0.1094   0.0297   0.1614
   2.750   0.7965   0.01718   0.00908  -0.1093   0.0296   0.2748
   3.000   0.8212   0.01716   0.00962  -0.1096   0.0295   0.5358
   3.500   0.8644   0.01716   0.01054  -0.1080   0.0294   1.0000
   3.750   0.8889   0.01770   0.01101  -0.1078   0.0294   1.0000
   4.000   0.9136   0.01825   0.01151  -0.1077   0.0293   1.0000
   4.250   0.9385   0.01882   0.01202  -0.1076   0.0293   1.0000
   4.500   0.9635   0.01941   0.01256  -0.1076   0.0292   1.0000
   4.750   0.9887   0.02002   0.01311  -0.1076   0.0292   1.0000
   5.000   1.0140   0.02065   0.01370  -0.1077   0.0291   1.0000
   5.250   1.0394   0.02130   0.01430  -0.1078   0.0291   1.0000
   5.500   1.0649   0.02196   0.01492  -0.1079   0.0291   1.0000
   5.750   1.0905   0.02265   0.01558  -0.1081   0.0290   1.0000
   6.000   1.1160   0.02335   0.01624  -0.1083   0.0290   1.0000
   6.250   1.1418   0.02413   0.01698  -0.1085   0.0290   1.0000
   6.750   1.1627   0.01730   0.01023  -0.1039   0.0286   1.0000
   7.000   1.2217   0.02754   0.02025  -0.1099   0.0286   1.0000
   7.250   1.2456   0.02795   0.02067  -0.1098   0.0285   1.0000
   7.500   1.2688   0.02817   0.02092  -0.1096   0.0284   1.0000
   7.750   1.2911   0.02824   0.02100  -0.1092   0.0271   1.0000
   8.000   1.3137   0.02859   0.02136  -0.1090   0.0253   1.0000
   8.250   1.3363   0.02910   0.02187  -0.1088   0.0245   1.0000
   8.500   1.3595   0.02949   0.02227  -0.1087   0.0234   1.0000
   8.750   1.3813   0.02981   0.02258  -0.1084   0.0224   1.0000
   9.000   1.4090   0.03100   0.02378  -0.1092   0.0195   1.0000
   9.500   1.4509   0.03138   0.02407  -0.1083   0.0122   1.0000
   9.750   1.4729   0.03186   0.02450  -0.1081   0.0108   1.0000
  10.000   1.4960   0.03255   0.02518  -0.1082   0.0100   1.0000
  10.250   1.5189   0.03324   0.02586  -0.1082   0.0092   1.0000
  10.500   1.5410   0.03386   0.02645  -0.1080   0.0085   1.0000
  10.750   1.5626   0.03442   0.02700  -0.1078   0.0079   1.0000
  11.000   1.5851   0.03516   0.02774  -0.1078   0.0075   1.0000
  11.250   1.6071   0.03587   0.02845  -0.1077   0.0072   1.0000
  11.500   1.6289   0.03657   0.02916  -0.1076   0.0068   1.0000
  11.750   1.6503   0.03727   0.02984  -0.1075   0.0065   1.0000
  12.000   1.6713   0.03795   0.03051  -0.1073   0.0061   1.0000
  12.250   1.6914   0.03857   0.03113  -0.1069   0.0058   1.0000
  12.500   1.7131   0.03943   0.03200  -0.1069   0.0056   1.0000
  12.750   1.7347   0.04032   0.03291  -0.1069   0.0054   1.0000
  13.000   1.7558   0.04121   0.03382  -0.1068   0.0053   1.0000
  13.250   1.7767   0.04213   0.03476  -0.1067   0.0051   1.0000
  13.500   1.7976   0.04309   0.03574  -0.1067   0.0048   1.0000
  13.750   1.8184   0.04411   0.03677  -0.1067   0.0046   1.0000
  14.000   1.8388   0.04514   0.03781  -0.1066   0.0044   1.0000
  14.250   1.8583   0.04615   0.03885  -0.1064   0.0043   1.0000
  14.500   1.8768   0.04710   0.03982  -0.1060   0.0041   1.0000
  14.750   1.8937   0.04787   0.04061  -0.1054   0.0039   1.0000
  15.000   1.9110   0.04882   0.04159  -0.1049   0.0038   1.0000
  15.250   1.9293   0.04998   0.04280  -0.1046   0.0038   1.0000
  15.500   1.9472   0.05118   0.04405  -0.1043   0.0037   1.0000
  15.750   1.9644   0.05239   0.04532  -0.1039   0.0036   1.0000
  16.000   1.9811   0.05363   0.04662  -0.1035   0.0035   1.0000
  16.250   1.9971   0.05490   0.04796  -0.1030   0.0034   1.0000
  16.500   2.0126   0.05619   0.04932  -0.1024   0.0034   1.0000
  16.750   2.0273   0.05753   0.05072  -0.1018   0.0033   1.0000
  17.000   2.0413   0.05890   0.05216  -0.1011   0.0032   1.0000
  17.250   2.0541   0.06031   0.05365  -0.1003   0.0031   1.0000
  17.500   2.0660   0.06178   0.05520  -0.0994   0.0031   1.0000
  17.750   2.0769   0.06330   0.05679  -0.0984   0.0030   1.0000
  18.000   2.0866   0.06485   0.05843  -0.0973   0.0029   1.0000
  18.250   2.0949   0.06646   0.06014  -0.0960   0.0029   1.0000
  18.500   2.1011   0.06809   0.06186  -0.0946   0.0028   1.0000
  18.750   2.1049   0.06974   0.06361  -0.0928   0.0028   1.0000
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