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FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il)
Reynolds number: 500,000
Max Cl/Cd: 125.58 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63137sm-il-500000.txt
Download as CSV file: xf-fx63137sm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-137 13.7% smoothed                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1518   0.11270   0.11034  -0.0708   0.9862   0.0220
 -10.500  -0.1396   0.10831   0.10595  -0.0747   0.9830   0.0228
 -10.250  -0.1405   0.09998   0.09763  -0.0829   0.9780   0.0237
 -10.000  -0.1214   0.09719   0.09484  -0.0852   0.9759   0.0240
  -9.750  -0.0150   0.07407   0.07181  -0.1027   0.9408   0.0280
  -9.500   0.0070   0.07127   0.06900  -0.1044   0.9376   0.0284
  -9.250   0.0261   0.06800   0.06571  -0.1073   0.9313   0.0288
  -9.000   0.0474   0.06410   0.06178  -0.1118   0.9264   0.0298
  -8.750   0.0660   0.05846   0.05611  -0.1185   0.9224   0.0312
  -8.500   0.0565   0.04528   0.04289  -0.1319   0.9139   0.0333
  -8.250   0.0873   0.04254   0.04009  -0.1370   0.9060   0.0339
  -8.000  -0.0378   0.02802   0.02420  -0.1810   0.8938   0.0240
  -7.750  -0.0100   0.02538   0.02140  -0.1838   0.8839   0.0227
  -7.500   0.0210   0.02147   0.01695  -0.1887   0.8745   0.0221
  -7.250   0.0481   0.01930   0.01440  -0.1905   0.8648   0.0224
  -7.000   0.0812   0.01778   0.01250  -0.1928   0.8575   0.0231
  -6.750   0.1086   0.01655   0.01103  -0.1934   0.8490   0.0233
  -6.500   0.1397   0.01567   0.00990  -0.1944   0.8418   0.0236
  -6.250   0.1671   0.01436   0.00850  -0.1949   0.8346   0.0241
  -6.000   0.1958   0.01368   0.00778  -0.1954   0.8273   0.0248
  -5.750   0.2260   0.01316   0.00718  -0.1961   0.8210   0.0256
  -5.500   0.2546   0.01266   0.00663  -0.1964   0.8138   0.0266
  -5.250   0.2852   0.01236   0.00620  -0.1970   0.8074   0.0278
  -5.000   0.3159   0.01170   0.00554  -0.1981   0.8010   0.0293
  -4.750   0.3464   0.01133   0.00514  -0.1988   0.7943   0.0310
  -4.250   0.4101   0.01058   0.00430  -0.2008   0.7818   0.0358
  -4.000   0.4419   0.01027   0.00394  -0.2018   0.7754   0.0404
  -3.750   0.4743   0.01001   0.00365  -0.2029   0.7696   0.0492
  -3.500   0.5069   0.00959   0.00336  -0.2041   0.7630   0.0822
  -3.250   0.5416   0.00911   0.00312  -0.2061   0.7569   0.1680
  -3.000   0.5768   0.00860   0.00301  -0.2082   0.7508   0.3065
  -2.750   0.6074   0.00847   0.00301  -0.2089   0.7442   0.3708
  -2.500   0.6374   0.00849   0.00300  -0.2093   0.7381   0.4052
  -2.250   0.6664   0.00850   0.00303  -0.2094   0.7316   0.4303
  -2.000   0.6952   0.00854   0.00305  -0.2095   0.7250   0.4533
  -1.750   0.7244   0.00862   0.00308  -0.2096   0.7189   0.4708
  -1.500   0.7527   0.00863   0.00311  -0.2096   0.7120   0.4828
  -1.250   0.7814   0.00870   0.00311  -0.2096   0.7055   0.4943
  -1.000   0.8099   0.00878   0.00316  -0.2096   0.6990   0.5081
  -0.750   0.8380   0.00883   0.00323  -0.2096   0.6919   0.5223
  -0.500   0.8666   0.00892   0.00325  -0.2096   0.6855   0.5317
  -0.250   0.8946   0.00894   0.00330  -0.2095   0.6782   0.5404
   0.000   0.9228   0.00902   0.00332  -0.2095   0.6713   0.5488
   0.250   0.9508   0.00907   0.00338  -0.2095   0.6643   0.5570
   0.500   0.9787   0.00914   0.00342  -0.2094   0.6567   0.5655
   0.750   1.0066   0.00923   0.00350  -0.2093   0.6496   0.5737
   1.000   1.0343   0.00929   0.00355  -0.2092   0.6416   0.5825
   1.250   1.0618   0.00940   0.00364  -0.2091   0.6344   0.5909
   1.500   1.0894   0.00947   0.00371  -0.2090   0.6261   0.5998
   1.750   1.1166   0.00959   0.00381  -0.2088   0.6184   0.6083
   2.000   1.1439   0.00966   0.00391  -0.2086   0.6099   0.6178
   2.250   1.1707   0.00980   0.00402  -0.2084   0.6019   0.6266
   2.500   1.1979   0.00989   0.00414  -0.2082   0.5931   0.6360
   2.750   1.2243   0.01004   0.00427  -0.2079   0.5848   0.6457
   3.000   1.2511   0.01014   0.00440  -0.2076   0.5756   0.6554
   3.250   1.2774   0.01030   0.00455  -0.2073   0.5670   0.6655
   3.500   1.3036   0.01042   0.00471  -0.2069   0.5574   0.6754
   3.750   1.3293   0.01059   0.00486  -0.2065   0.5466   0.6866
   4.000   1.3538   0.01078   0.00504  -0.2058   0.5338   0.6971
   4.250   1.3781   0.01099   0.00522  -0.2051   0.5197   0.7078
   4.750   1.4264   0.01141   0.00564  -0.2037   0.4909   0.7315
   5.000   1.4502   0.01166   0.00588  -0.2029   0.4770   0.7435
   5.250   1.4736   0.01192   0.00613  -0.2021   0.4638   0.7563
   5.500   1.4965   0.01221   0.00641  -0.2012   0.4508   0.7702
   5.750   1.5190   0.01250   0.00670  -0.2002   0.4376   0.7840
   6.000   1.5413   0.01278   0.00700  -0.1992   0.4238   0.7986
   6.250   1.5626   0.01311   0.00733  -0.1981   0.4091   0.8147
   6.500   1.5829   0.01346   0.00768  -0.1967   0.3937   0.8325
   6.750   1.6023   0.01383   0.00804  -0.1952   0.3787   0.8524
   7.000   1.6199   0.01419   0.00842  -0.1933   0.3640   0.8779
   7.250   1.6268   0.01437   0.00866  -0.1891   0.3510   1.0000
   7.500   1.6447   0.01490   0.00912  -0.1875   0.3349   1.0000
   7.750   1.6610   0.01547   0.00962  -0.1856   0.3180   1.0000
   8.000   1.6762   0.01610   0.01018  -0.1836   0.3001   1.0000
   8.250   1.6901   0.01679   0.01080  -0.1813   0.2822   1.0000
   8.500   1.7029   0.01756   0.01149  -0.1790   0.2642   1.0000
   8.750   1.7141   0.01842   0.01227  -0.1765   0.2458   1.0000
   9.000   1.7236   0.01941   0.01316  -0.1738   0.2269   1.0000
   9.250   1.7326   0.02046   0.01413  -0.1711   0.2064   1.0000
   9.500   1.7384   0.02175   0.01530  -0.1681   0.1845   1.0000
   9.750   1.7425   0.02320   0.01664  -0.1650   0.1626   1.0000
  10.000   1.7452   0.02483   0.01816  -0.1620   0.1427   1.0000
  10.250   1.7487   0.02649   0.01974  -0.1592   0.1280   1.0000
  10.500   1.7540   0.02809   0.02132  -0.1569   0.1180   1.0000
  10.750   1.7589   0.02980   0.02302  -0.1546   0.1107   1.0000
  11.000   1.7658   0.03140   0.02465  -0.1527   0.1054   1.0000
  11.250   1.7685   0.03344   0.02669  -0.1505   0.1004   1.0000
  11.500   1.7765   0.03506   0.02839  -0.1490   0.0973   1.0000
  11.750   1.7835   0.03684   0.03023  -0.1474   0.0943   1.0000
  12.000   1.7879   0.03892   0.03236  -0.1458   0.0914   1.0000
  12.250   1.7880   0.04149   0.03496  -0.1441   0.0884   1.0000
  12.500   1.7931   0.04365   0.03720  -0.1428   0.0865   1.0000
  12.750   1.8005   0.04562   0.03927  -0.1417   0.0849   1.0000
  13.000   1.8064   0.04780   0.04154  -0.1407   0.0832   1.0000
  13.250   1.8103   0.05025   0.04407  -0.1397   0.0815   1.0000
  13.500   1.8125   0.05297   0.04685  -0.1387   0.0799   1.0000
  13.750   1.8115   0.05615   0.05008  -0.1378   0.0781   1.0000
  14.000   1.8067   0.05988   0.05388  -0.1369   0.0761   1.0000
  14.250   1.8138   0.06220   0.05632  -0.1364   0.0753   1.0000
  14.500   1.8189   0.06483   0.05905  -0.1360   0.0743   1.0000
  14.750   1.8228   0.06766   0.06199  -0.1356   0.0732   1.0000
  15.000   1.8265   0.07056   0.06499  -0.1353   0.0719   1.0000
  15.250   1.8297   0.07358   0.06809  -0.1352   0.0706   1.0000
  15.500   1.8311   0.07688   0.07145  -0.1351   0.0692   1.0000
  15.750   1.8295   0.08064   0.07525  -0.1352   0.0676   1.0000
  16.000   1.8258   0.08466   0.07933  -0.1351   0.0658   1.0000
  16.250   1.8318   0.08751   0.08232  -0.1354   0.0647   1.0000
  16.500   1.8362   0.09059   0.08551  -0.1358   0.0633   1.0000
  16.750   1.8395   0.09382   0.08884  -0.1363   0.0618   1.0000
  17.000   1.8412   0.09734   0.09243  -0.1369   0.0603   1.0000
  17.250   1.8406   0.10121   0.09635  -0.1376   0.0588   1.0000
  17.500   1.8378   0.10537   0.10055  -0.1384   0.0574   1.0000
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