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GOE 405 AIRFOIL (goe405-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 405 AIRFOIL (goe405-il)
Reynolds number: 1,000,000
Max Cl/Cd: 137.49 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe405-il-1000000.txt
Download as CSV file: xf-goe405-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 405 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1070   0.10336   0.10167  -0.0843   0.9757   0.0142
 -10.500  -0.0930   0.10008   0.09839  -0.0874   0.9733   0.0150
 -10.250  -0.3524   0.02283   0.02000  -0.1531   0.9218   0.0128
 -10.000  -0.3335   0.02102   0.01794  -0.1531   0.9148   0.0131
  -9.750  -0.3238   0.01822   0.01478  -0.1522   0.9065   0.0137
  -9.500  -0.3004   0.01758   0.01406  -0.1518   0.9002   0.0142
  -9.250  -0.2760   0.01716   0.01357  -0.1515   0.8940   0.0146
  -9.000  -0.2526   0.01658   0.01289  -0.1510   0.8869   0.0151
  -8.750  -0.2288   0.01597   0.01214  -0.1506   0.8803   0.0157
  -8.500  -0.2058   0.01531   0.01132  -0.1499   0.8727   0.0162
  -8.250  -0.1803   0.01499   0.01087  -0.1496   0.8658   0.0166
  -8.000  -0.1610   0.01369   0.00937  -0.1486   0.8570   0.0175
  -7.750  -0.1350   0.01355   0.00919  -0.1483   0.8493   0.0182
  -7.500  -0.1093   0.01336   0.00894  -0.1479   0.8408   0.0189
  -7.250  -0.0838   0.01309   0.00857  -0.1474   0.8320   0.0197
  -7.000  -0.0578   0.01298   0.00835  -0.1471   0.8229   0.0205
  -6.750  -0.0317   0.01290   0.00817  -0.1466   0.8124   0.0210
  -6.500  -0.0109   0.01177   0.00686  -0.1456   0.8015   0.0223
  -6.250   0.0143   0.01159   0.00661  -0.1451   0.7904   0.0231
  -5.750   0.0654   0.01123   0.00606  -0.1441   0.7698   0.0251
  -5.500   0.0916   0.01114   0.00588  -0.1437   0.7617   0.0259
  -5.250   0.1162   0.01057   0.00517  -0.1432   0.7543   0.0269
  -5.000   0.1406   0.01006   0.00457  -0.1426   0.7476   0.0282
  -4.750   0.1669   0.00987   0.00435  -0.1423   0.7407   0.0294
  -4.250   0.2193   0.00948   0.00382  -0.1415   0.7284   0.0315
  -4.000   0.2455   0.00931   0.00358  -0.1412   0.7224   0.0323
  -3.750   0.2723   0.00924   0.00347  -0.1409   0.7169   0.0329
  -3.500   0.2974   0.00873   0.00287  -0.1403   0.7111   0.0347
  -3.250   0.3233   0.00854   0.00262  -0.1399   0.7056   0.0362
  -3.000   0.3499   0.00839   0.00244  -0.1396   0.7003   0.0377
  -2.750   0.3765   0.00827   0.00228  -0.1393   0.6946   0.0393
  -2.500   0.4028   0.00819   0.00214  -0.1389   0.6893   0.0405
  -2.250   0.4296   0.00804   0.00197  -0.1386   0.6843   0.0428
  -2.000   0.4558   0.00790   0.00182  -0.1383   0.6787   0.0479
  -1.750   0.4815   0.00778   0.00171  -0.1378   0.6731   0.0628
  -1.500   0.5074   0.00756   0.00166  -0.1375   0.6674   0.1081
  -1.250   0.5336   0.00753   0.00165  -0.1371   0.6615   0.1244
  -1.000   0.5601   0.00752   0.00163  -0.1368   0.6556   0.1352
  -0.750   0.5867   0.00751   0.00162  -0.1366   0.6491   0.1446
  -0.500   0.6126   0.00753   0.00162  -0.1361   0.6429   0.1541
  -0.250   0.6394   0.00752   0.00162  -0.1359   0.6361   0.1627
   0.000   0.6650   0.00755   0.00164  -0.1354   0.6288   0.1735
   0.250   0.6915   0.00755   0.00165  -0.1352   0.6214   0.1819
   0.500   0.7167   0.00760   0.00167  -0.1346   0.6133   0.1899
   0.750   0.7427   0.00760   0.00168  -0.1343   0.6042   0.1990
   1.000   0.7679   0.00766   0.00171  -0.1337   0.5944   0.2082
   1.250   0.7922   0.00772   0.00175  -0.1330   0.5828   0.2172
   1.500   0.8168   0.00778   0.00178  -0.1324   0.5702   0.2255
   1.750   0.8413   0.00785   0.00183  -0.1318   0.5577   0.2350
   2.000   0.8653   0.00793   0.00190  -0.1310   0.5450   0.2473
   2.250   0.8890   0.00801   0.00197  -0.1302   0.5319   0.2621
   2.750   0.9347   0.00816   0.00216  -0.1284   0.5050   0.3279
   3.000   0.9899   0.00720   0.00256  -0.1353   0.4884   1.0000
   3.250   1.0112   0.00739   0.00267  -0.1340   0.4759   1.0000
   3.750   1.0550   0.00773   0.00291  -0.1317   0.4548   1.0000
   4.000   1.0766   0.00792   0.00304  -0.1305   0.4456   1.0000
   4.250   1.0983   0.00809   0.00318  -0.1294   0.4368   1.0000
   4.500   1.1203   0.00826   0.00331  -0.1283   0.4289   1.0000
   4.750   1.1417   0.00845   0.00347  -0.1271   0.4214   1.0000
   5.000   1.1638   0.00861   0.00361  -0.1260   0.4149   1.0000
   5.250   1.1842   0.00881   0.00378  -0.1247   0.4064   1.0000
   5.500   1.2037   0.00900   0.00395  -0.1231   0.3960   1.0000
   5.750   1.2219   0.00922   0.00413  -0.1213   0.3877   1.0000
   6.000   1.2415   0.00941   0.00430  -0.1198   0.3777   1.0000
   6.250   1.2610   0.00962   0.00449  -0.1183   0.3702   1.0000
   6.500   1.2786   0.00989   0.00472  -0.1164   0.3588   1.0000
   6.750   1.2974   0.01014   0.00494  -0.1149   0.3461   1.0000
   7.000   1.3145   0.01046   0.00519  -0.1130   0.3313   1.0000
   7.250   1.3320   0.01078   0.00547  -0.1113   0.3174   1.0000
   7.500   1.3472   0.01119   0.00581  -0.1092   0.3004   1.0000
   7.750   1.3613   0.01167   0.00619  -0.1069   0.2788   1.0000
   8.000   1.3706   0.01238   0.00673  -0.1039   0.2498   1.0000
   8.250   1.3755   0.01331   0.00744  -0.1003   0.2148   1.0000
   8.500   1.3767   0.01448   0.00835  -0.0963   0.1730   1.0000
   8.750   1.3612   0.01659   0.00999  -0.0901   0.0988   1.0000
   9.000   1.3449   0.01895   0.01201  -0.0841   0.0315   1.0000
   9.250   1.3529   0.02001   0.01302  -0.0817   0.0192   1.0000
   9.500   1.3645   0.02089   0.01392  -0.0799   0.0169   1.0000
   9.750   1.3757   0.02183   0.01491  -0.0780   0.0153   1.0000
  10.000   1.3889   0.02265   0.01577  -0.0765   0.0144   1.0000
  10.250   1.3998   0.02365   0.01682  -0.0749   0.0135   1.0000
  10.500   1.4093   0.02479   0.01801  -0.0731   0.0127   1.0000
  10.750   1.4164   0.02613   0.01942  -0.0712   0.0122   1.0000
  11.000   1.4221   0.02762   0.02100  -0.0693   0.0116   1.0000
  11.250   1.4314   0.02889   0.02232  -0.0679   0.0114   1.0000
  11.500   1.4400   0.03025   0.02375  -0.0665   0.0110   1.0000
  11.750   1.4473   0.03175   0.02531  -0.0651   0.0106   1.0000
  12.000   1.4540   0.03334   0.02696  -0.0638   0.0102   1.0000
  12.250   1.4599   0.03507   0.02875  -0.0625   0.0098   1.0000
  12.500   1.4631   0.03709   0.03084  -0.0612   0.0094   1.0000
  12.750   1.4583   0.03993   0.03377  -0.0596   0.0090   1.0000
  13.000   1.4490   0.04337   0.03734  -0.0580   0.0089   1.0000
  13.250   1.4446   0.04642   0.04049  -0.0569   0.0088   1.0000
  13.500   1.4530   0.04817   0.04229  -0.0563   0.0086   1.0000
  13.750   1.4531   0.05085   0.04506  -0.0555   0.0084   1.0000
  14.000   1.4543   0.05349   0.04778  -0.0550   0.0082   1.0000
  14.250   1.4489   0.05696   0.05135  -0.0543   0.0082   1.0000
  14.500   1.4491   0.05981   0.05427  -0.0539   0.0079   1.0000
  14.750   1.4458   0.06314   0.05769  -0.0536   0.0077   1.0000
  15.000   1.4446   0.06630   0.06093  -0.0534   0.0075   1.0000
  15.250   1.4400   0.06995   0.06466  -0.0533   0.0074   1.0000
  15.500   1.4349   0.07369   0.06849  -0.0533   0.0073   1.0000
  15.750   1.4298   0.07750   0.07238  -0.0534   0.0072   1.0000
  16.000   1.4253   0.08131   0.07626  -0.0537   0.0071   1.0000
  16.250   1.4197   0.08530   0.08034  -0.0540   0.0070   1.0000
  16.500   1.4146   0.08928   0.08439  -0.0544   0.0069   1.0000
  16.750   1.4101   0.09318   0.08836  -0.0549   0.0068   1.0000
  17.000   1.4033   0.09743   0.09267  -0.0555   0.0067   1.0000
  17.250   1.3963   0.10163   0.09694  -0.0560   0.0066   1.0000
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