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FX 74-CL6-140 (fx74cl6140-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 74-CL6-140 (fx74cl6140-il)
Reynolds number: 500,000
Max Cl/Cd: 114.75 at α=11.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74cl6140-il-500000.txt
Download as CSV file: xf-fx74cl6140-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 74-CL6-140                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.0644   0.09408   0.08976  -0.0757   0.5279   0.0146
  -9.750   0.0640   0.09062   0.08631  -0.0779   0.5270   0.0151
  -9.500   0.0638   0.08737   0.08308  -0.0798   0.5260   0.0152
  -9.250   0.0785   0.08424   0.07996  -0.0793   0.5240   0.0154
  -9.000   0.0866   0.08149   0.07720  -0.0799   0.5225   0.0156
  -8.750   0.0940   0.07876   0.07448  -0.0806   0.5209   0.0158
  -8.500   0.1010   0.07604   0.07176  -0.0814   0.5194   0.0162
  -8.250   0.1075   0.07329   0.06900  -0.0822   0.5180   0.0171
  -8.000   0.1126   0.07029   0.06601  -0.0832   0.5167   0.0175
  -7.750   0.1117   0.06690   0.06263  -0.0853   0.5156   0.0181
  -7.500   0.1099   0.06338   0.05913  -0.0877   0.5145   0.0183
  -7.250   0.1153   0.06026   0.05600  -0.0882   0.5128   0.0184
  -7.000   0.1259   0.05792   0.05366  -0.0878   0.5112   0.0186
  -6.750   0.1335   0.05543   0.05119  -0.0881   0.5100   0.0188
  -6.500   0.1389   0.05289   0.04868  -0.0887   0.5087   0.0191
  -6.250   0.1427   0.05034   0.04616  -0.0892   0.5075   0.0194
  -6.000   0.1435   0.04790   0.04375  -0.0895   0.5063   0.0198
  -5.750   0.1488   0.04495   0.04083  -0.0916   0.5051   0.0201
  -5.500   0.1565   0.04143   0.03731  -0.0955   0.5039   0.0208
  -5.250   0.1744   0.03223   0.02795  -0.1129   0.5034   0.0217
  -5.000   0.1870   0.03001   0.02574  -0.1129   0.5019   0.0220
  -4.750   0.2044   0.02790   0.02359  -0.1142   0.5004   0.0224
  -4.500   0.2257   0.02516   0.02076  -0.1170   0.4991   0.0230
  -4.250   0.2603   0.01840   0.01355  -0.1253   0.4981   0.0258
  -4.000   0.2825   0.01713   0.01225  -0.1262   0.4963   0.0263
  -3.750   0.3090   0.01546   0.01044  -0.1280   0.4943   0.0278
  -3.500   0.3426   0.01227   0.00688  -0.1315   0.4933   0.0308
  -3.250   0.3765   0.01020   0.00437  -0.1340   0.4921   0.0352
  -3.000   0.4031   0.00942   0.00363  -0.1349   0.4907   0.0364
  -2.750   0.4346   0.00830   0.00222  -0.1364   0.4893   0.0417
  -2.500   0.4875   0.01704   0.00977  -0.1440   0.4892   0.0246
  -2.250   0.5180   0.01570   0.00821  -0.1443   0.4878   0.0235
  -2.000   0.5477   0.01493   0.00729  -0.1445   0.4863   0.0237
  -1.750   0.5771   0.01440   0.00665  -0.1447   0.4847   0.0241
  -1.500   0.6064   0.01413   0.00628  -0.1448   0.4831   0.0253
  -1.250   0.6358   0.01367   0.00579  -0.1452   0.4816   0.0262
  -1.000   0.6654   0.01341   0.00552  -0.1456   0.4801   0.0271
  -0.750   0.6951   0.01334   0.00539  -0.1460   0.4784   0.0288
  -0.500   0.7249   0.01320   0.00525  -0.1464   0.4771   0.0314
  -0.250   0.7544   0.01303   0.00510  -0.1467   0.4759   0.0367
   0.000   0.7851   0.01261   0.00501  -0.1475   0.4745   0.1310
   0.250   0.8170   0.01178   0.00508  -0.1492   0.4729   0.4850
   0.500   0.8446   0.01167   0.00542  -0.1491   0.4714   0.6959
   0.750   0.8719   0.01182   0.00558  -0.1487   0.4699   0.7380
   1.000   0.8984   0.01192   0.00572  -0.1482   0.4685   0.7663
   1.250   0.9255   0.01201   0.00579  -0.1479   0.4670   0.7847
   1.500   0.9529   0.01209   0.00584  -0.1477   0.4655   0.7968
   1.750   0.9801   0.01220   0.00592  -0.1475   0.4640   0.8104
   2.000   1.0071   0.01237   0.00607  -0.1473   0.4626   0.8245
   2.250   1.0346   0.01264   0.00632  -0.1473   0.4609   0.8342
   2.500   1.0627   0.01268   0.00638  -0.1474   0.4597   0.8379
   2.750   1.0905   0.01273   0.00645  -0.1475   0.4582   0.8414
   3.000   1.1184   0.01281   0.00655  -0.1476   0.4566   0.8454
   3.250   1.1465   0.01291   0.00666  -0.1478   0.4551   0.8494
   3.500   1.1746   0.01301   0.00676  -0.1480   0.4534   0.8535
   3.750   1.2022   0.01308   0.00684  -0.1481   0.4518   0.8583
   4.000   1.2300   0.01315   0.00692  -0.1482   0.4502   0.8646
   4.250   1.2576   0.01324   0.00701  -0.1483   0.4487   0.8717
   4.500   1.2848   0.01337   0.00714  -0.1483   0.4473   0.8813
   4.750   1.3111   0.01362   0.00742  -0.1482   0.4454   0.8974
   5.000   1.3373   0.01362   0.00755  -0.1480   0.4440   1.0000
   5.250   1.3654   0.01375   0.00771  -0.1483   0.4424   1.0000
   5.500   1.3934   0.01390   0.00791  -0.1486   0.4406   1.0000
   5.750   1.4212   0.01406   0.00809  -0.1489   0.4388   1.0000
   6.000   1.4490   0.01419   0.00823  -0.1491   0.4370   1.0000
   6.250   1.4768   0.01432   0.00836  -0.1494   0.4352   1.0000
   6.500   1.5047   0.01445   0.00850  -0.1496   0.4335   1.0000
   6.750   1.5324   0.01464   0.00867  -0.1499   0.4320   1.0000
   7.000   1.5601   0.01496   0.00897  -0.1502   0.4301   1.0000
   7.250   1.5861   0.01516   0.00926  -0.1502   0.4283   1.0000
   7.500   1.6118   0.01531   0.00949  -0.1501   0.4263   1.0000
   7.750   1.6377   0.01548   0.00973  -0.1500   0.4242   1.0000
   8.000   1.6639   0.01563   0.00994  -0.1500   0.4222   1.0000
   8.250   1.6902   0.01577   0.01011  -0.1500   0.4201   1.0000
   8.500   1.7168   0.01589   0.01025  -0.1501   0.4181   1.0000
   8.750   1.7434   0.01607   0.01045  -0.1502   0.4162   1.0000
   9.000   1.7695   0.01640   0.01080  -0.1503   0.4139   1.0000
   9.250   1.7929   0.01657   0.01111  -0.1498   0.4117   1.0000
   9.500   1.8169   0.01673   0.01138  -0.1495   0.4090   1.0000
   9.750   1.8413   0.01682   0.01152  -0.1492   0.4060   1.0000
  10.000   1.8660   0.01675   0.01147  -0.1489   0.4023   1.0000
  10.250   1.8884   0.01682   0.01160  -0.1483   0.3975   1.0000
  10.500   1.9094   0.01683   0.01171  -0.1474   0.3920   1.0000
  10.750   1.9312   0.01685   0.01175  -0.1466   0.3868   1.0000
  11.000   1.9512   0.01703   0.01204  -0.1457   0.3812   1.0000
  11.250   1.9703   0.01717   0.01224  -0.1445   0.3741   1.0000
  11.500   1.9886   0.01743   0.01257  -0.1433   0.3677   1.0000
  11.750   2.0066   0.01775   0.01297  -0.1421   0.3616   1.0000
  12.000   2.0212   0.01815   0.01341  -0.1403   0.3559   1.0000
  12.250   2.0337   0.01856   0.01393  -0.1382   0.3487   1.0000
  12.500   2.0409   0.01915   0.01454  -0.1353   0.3416   1.0000
  12.750   2.0485   0.01981   0.01529  -0.1327   0.3332   1.0000
  13.000   2.0518   0.02072   0.01625  -0.1296   0.3250   1.0000
  13.250   2.0501   0.02199   0.01754  -0.1264   0.3157   1.0000
  13.500   2.0472   0.02354   0.01916  -0.1234   0.3052   1.0000
  13.750   2.0388   0.02568   0.02134  -0.1205   0.2950   1.0000
  14.000   2.0243   0.02867   0.02436  -0.1179   0.2847   1.0000
  14.250   2.0057   0.03250   0.02824  -0.1160   0.2736   1.0000
  14.500   1.9847   0.03703   0.03283  -0.1147   0.2626   1.0000
  14.750   1.9584   0.04246   0.03831  -0.1137   0.2522   1.0000
  15.000   1.9291   0.04842   0.04431  -0.1130   0.2433   1.0000
  15.250   1.8991   0.05462   0.05055  -0.1125   0.2325   1.0000
  15.500   1.8706   0.06087   0.05683  -0.1123   0.2214   1.0000
  15.750   1.8430   0.06730   0.06327  -0.1125   0.2097   1.0000
  16.000   1.8162   0.07389   0.06985  -0.1129   0.1971   1.0000
  16.250   1.7911   0.08049   0.07643  -0.1136   0.1840   1.0000
  16.500   1.7669   0.08718   0.08309  -0.1145   0.1701   1.0000
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