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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 500,000
Max Cl/Cd: 41.6 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe388-il-500000-n5.txt
Download as CSV file: xf-goe388-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2742   0.10027   0.09494  -0.0428   0.0496   0.0164
  -9.250  -0.2706   0.09641   0.09109  -0.0449   0.0493   0.0170
  -9.000  -0.2762   0.09014   0.08484  -0.0491   0.0500   0.0183
  -8.750  -0.2648   0.08840   0.08310  -0.0499   0.0487   0.0185
  -8.500  -0.2544   0.08638   0.08110  -0.0510   0.0475   0.0188
  -8.250  -0.2455   0.08393   0.07865  -0.0525   0.0471   0.0192
  -8.000  -0.2383   0.08099   0.07572  -0.0546   0.0464   0.0195
  -7.750  -0.2336   0.07805   0.07280  -0.0568   0.0459   0.0198
  -7.500  -0.2236   0.07445   0.06922  -0.0609   0.0456   0.0201
  -7.250  -0.2113   0.07036   0.06511  -0.0661   0.0454   0.0206
  -7.000  -0.1963   0.06557   0.06029  -0.0725   0.0451   0.0211
  -6.750  -0.1761   0.05663   0.05124  -0.0848   0.0452   0.0226
  -6.500  -0.1521   0.04663   0.04102  -0.0963   0.0453   0.0233
  -6.250  -0.1294   0.04071   0.03490  -0.1017   0.0447   0.0237
  -6.000  -0.1055   0.03690   0.03090  -0.1046   0.0439   0.0241
  -5.750  -0.0812   0.03511   0.02900  -0.1059   0.0434   0.0245
  -5.500  -0.0562   0.03253   0.02624  -0.1075   0.0423   0.0251
  -5.250  -0.0311   0.02796   0.02125  -0.1096   0.0415   0.0257
  -5.000  -0.0055   0.02501   0.01792  -0.1106   0.0408   0.0262
  -4.750   0.0205   0.02292   0.01550  -0.1112   0.0399   0.0266
  -4.500   0.0466   0.02140   0.01371  -0.1115   0.0394   0.0270
  -4.250   0.0732   0.02013   0.01219  -0.1118   0.0392   0.0272
  -4.000   0.1000   0.01915   0.01098  -0.1119   0.0387   0.0275
  -3.750   0.1268   0.01850   0.01017  -0.1120   0.0381   0.0281
  -3.500   0.1535   0.01789   0.00941  -0.1120   0.0377   0.0284
  -3.000   0.2065   0.01691   0.00817  -0.1120   0.0372   0.0288
  -2.750   0.2333   0.01650   0.00766  -0.1120   0.0371   0.0291
  -2.500   0.2601   0.01620   0.00726  -0.1119   0.0370   0.0294
  -2.250   0.2868   0.01599   0.00697  -0.1119   0.0366   0.0296
  -2.000   0.3131   0.01566   0.00657  -0.1118   0.0359   0.0300
  -1.750   0.3388   0.01538   0.00624  -0.1117   0.0354   0.0307
  -1.500   0.3632   0.01550   0.00631  -0.1114   0.0352   0.0313
  -1.250   0.3886   0.01554   0.00630  -0.1112   0.0351   0.0318
  -1.000   0.4151   0.01545   0.00619  -0.1112   0.0350   0.0323
  -0.750   0.4414   0.01542   0.00613  -0.1111   0.0349   0.0329
  -0.500   0.4674   0.01544   0.00613  -0.1110   0.0347   0.0336
  -0.250   0.4928   0.01555   0.00622  -0.1109   0.0344   0.0347
   0.000   0.5179   0.01572   0.00636  -0.1106   0.0341   0.0357
   0.250   0.5426   0.01592   0.00653  -0.1103   0.0339   0.0365
   0.500   0.5670   0.01617   0.00673  -0.1100   0.0337   0.0374
   0.750   0.5910   0.01647   0.00700  -0.1096   0.0335   0.0383
   1.000   0.6147   0.01679   0.00727  -0.1092   0.0334   0.0404
   1.250   0.6380   0.01718   0.00763  -0.1087   0.0333   0.0442
   1.500   0.6610   0.01762   0.00804  -0.1082   0.0332   0.0493
   2.000   0.7068   0.01849   0.00907  -0.1074   0.0331   0.1608
   2.250   0.7301   0.01889   0.00972  -0.1072   0.0330   0.2913
   3.250   0.8219   0.01990   0.01197  -0.1054   0.0329   1.0000
   3.500   0.8467   0.02039   0.01240  -0.1052   0.0329   1.0000
   3.750   0.8717   0.02096   0.01289  -0.1052   0.0329   1.0000
   4.000   0.8968   0.02156   0.01342  -0.1052   0.0329   1.0000
   4.250   0.9221   0.02217   0.01396  -0.1052   0.0329   1.0000
   4.500   0.9476   0.02281   0.01453  -0.1053   0.0329   1.0000
   4.750   0.9731   0.02346   0.01512  -0.1054   0.0329   1.0000
   5.000   0.9988   0.02414   0.01575  -0.1055   0.0329   1.0000
   5.250   1.0245   0.02484   0.01639  -0.1057   0.0329   1.0000
   5.500   1.0503   0.02557   0.01706  -0.1059   0.0329   1.0000
   5.750   1.0760   0.02631   0.01776  -0.1061   0.0329   1.0000
   6.000   1.1018   0.02709   0.01850  -0.1063   0.0329   1.0000
   6.250   1.1275   0.02789   0.01926  -0.1065   0.0329   1.0000
   6.500   1.1532   0.02871   0.02005  -0.1068   0.0329   1.0000
   6.750   1.1789   0.02956   0.02087  -0.1070   0.0329   1.0000
   7.000   1.2027   0.03010   0.02143  -0.1069   0.0329   1.0000
   7.250   1.2245   0.03032   0.02170  -0.1065   0.0328   1.0000
   7.500   1.2471   0.03071   0.02212  -0.1062   0.0327   1.0000
   7.750   1.2701   0.03122   0.02266  -0.1060   0.0324   1.0000
   8.000   1.2940   0.03193   0.02339  -0.1060   0.0320   1.0000
   8.250   1.3190   0.03296   0.02442  -0.1063   0.0313   1.0000
   8.500   1.3493   0.03521   0.02658  -0.1076   0.0308   1.0000
   8.750   1.3668   0.03473   0.02623  -0.1064   0.0302   1.0000
   9.000   1.3867   0.03503   0.02656  -0.1058   0.0271   1.0000
   9.250   1.4074   0.03543   0.02702  -0.1054   0.0254   1.0000
   9.500   1.4277   0.03578   0.02740  -0.1049   0.0239   1.0000
   9.750   1.4494   0.03607   0.02773  -0.1046   0.0207   1.0000
  10.000   1.4724   0.03672   0.02839  -0.1046   0.0152   1.0000
  10.250   1.4904   0.03682   0.02844  -0.1038   0.0140   1.0000
  10.500   1.5088   0.03710   0.02870  -0.1031   0.0128   1.0000
  10.750   1.5293   0.03773   0.02932  -0.1027   0.0118   1.0000
  11.000   1.5489   0.03830   0.02987  -0.1022   0.0110   1.0000
  11.250   1.5680   0.03890   0.03048  -0.1017   0.0104   1.0000
  11.500   1.5895   0.03978   0.03138  -0.1016   0.0098   1.0000
  11.750   1.6099   0.04061   0.03225  -0.1013   0.0092   1.0000
  12.000   1.6290   0.04138   0.03304  -0.1008   0.0086   1.0000
  12.250   1.6458   0.04200   0.03367  -0.1000   0.0082   1.0000
  12.500   1.6615   0.04262   0.03432  -0.0990   0.0079   1.0000
  12.750   1.6809   0.04355   0.03530  -0.0986   0.0077   1.0000
  13.000   1.6992   0.04445   0.03627  -0.0981   0.0074   1.0000
  13.250   1.7165   0.04534   0.03721  -0.0975   0.0071   1.0000
  13.500   1.7329   0.04623   0.03815  -0.0967   0.0069   1.0000
  13.750   1.7485   0.04713   0.03910  -0.0959   0.0067   1.0000
  14.000   1.7632   0.04804   0.04006  -0.0949   0.0064   1.0000
  14.250   1.7770   0.04898   0.04106  -0.0939   0.0063   1.0000
  14.500   1.7888   0.04990   0.04203  -0.0926   0.0061   1.0000
  14.750   1.7970   0.05084   0.04305  -0.0908   0.0059   1.0000
  15.000   1.7997   0.05183   0.04413  -0.0882   0.0057   1.0000
  15.250   1.8174   0.05323   0.04562  -0.0880   0.0056   1.0000
  15.500   1.8326   0.05466   0.04714  -0.0874   0.0054   1.0000
  15.750   1.8441   0.05608   0.04866  -0.0863   0.0053   1.0000
  16.000   1.8519   0.05750   0.05018  -0.0847   0.0051   1.0000
  16.250   1.8573   0.05896   0.05175  -0.0829   0.0050   1.0000
  16.500   1.8611   0.06049   0.05340  -0.0809   0.0049   1.0000
  16.750   1.8636   0.06209   0.05512  -0.0789   0.0048   1.0000
  17.000   1.8646   0.06377   0.05693  -0.0769   0.0047   1.0000
  17.250   1.8639   0.06554   0.05884  -0.0748   0.0046   1.0000
  17.500   1.8619   0.06738   0.06081  -0.0728   0.0045   1.0000
  17.750   1.8585   0.06931   0.06288  -0.0709   0.0045   1.0000
  18.000   1.8535   0.07137   0.06507  -0.0690   0.0044   1.0000
  18.250   1.8473   0.07353   0.06736  -0.0672   0.0044   1.0000
  18.500   1.8398   0.07580   0.06977  -0.0655   0.0043   1.0000
  18.750   1.8306   0.07826   0.07238  -0.0640   0.0043   1.0000
  19.000   1.8201   0.08088   0.07514  -0.0627   0.0042   1.0000
  19.250   1.8085   0.08364   0.07804  -0.0616   0.0042   1.0000
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