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FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-140/20 (fx78k140-il)
Reynolds number: 200,000
Max Cl/Cd: 54.18 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k140-il-200000.txt
Download as CSV file: xf-fx78k140-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-140/20                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.1736   0.12444   0.12044  -0.0790   0.8215   0.0302
 -12.000  -0.1850   0.12316   0.11922  -0.0835   0.8203   0.0349
 -11.750  -0.1821   0.11983   0.11590  -0.0848   0.8191   0.0350
 -11.500  -0.1726   0.11609   0.11217  -0.0854   0.8180   0.0347
 -11.250  -0.1734   0.11380   0.10993  -0.0882   0.8166   0.0351
 -11.000  -0.1715   0.11067   0.10684  -0.0902   0.8154   0.0352
 -10.750  -0.1667   0.10746   0.10366  -0.0916   0.8141   0.0352
 -10.500  -0.1540   0.10195   0.09815  -0.0890   0.8133   0.0387
 -10.250  -0.1505   0.09922   0.09543  -0.0903   0.8120   0.0386
 -10.000  -0.1464   0.09645   0.09267  -0.0911   0.8106   0.0403
  -9.750  -0.1461   0.09338   0.08962  -0.0921   0.8090   0.0426
  -9.500  -0.1475   0.09023   0.08651  -0.0936   0.8078   0.0443
  -9.250  -0.1476   0.08736   0.08364  -0.0949   0.8067   0.0446
  -9.000  -0.1571   0.08390   0.08023  -0.0984   0.8055   0.0464
  -8.750  -0.1658   0.07996   0.07639  -0.1039   0.8034   0.0470
  -8.500  -0.1050   0.06002   0.05679  -0.0980   0.7972   0.0502
  -8.250  -0.1084   0.05650   0.05329  -0.0995   0.7957   0.0508
  -8.000  -0.2039   0.07245   0.06872  -0.1062   0.7966   0.0476
  -7.750  -0.2119   0.07014   0.06626  -0.1050   0.7951   0.0477
  -7.500  -0.2236   0.06414   0.06023  -0.1040   0.7936   0.0487
  -7.250  -0.2130   0.06122   0.05741  -0.1029   0.7925   0.0504
  -7.000  -0.2087   0.05914   0.05528  -0.1025   0.7901   0.0512
  -6.750  -0.2043   0.05726   0.05335  -0.1018   0.7879   0.0539
  -6.500  -0.2020   0.05521   0.05116  -0.1005   0.7855   0.0551
  -6.250  -0.2045   0.05574   0.05105  -0.0963   0.7826   0.0610
  -5.250  -0.2014   0.04249   0.03694  -0.0835   0.7727   0.0445
  -5.000  -0.2060   0.03882   0.03243  -0.0769   0.7701   0.0362
  -4.750  -0.1905   0.03752   0.03080  -0.0744   0.7681   0.0356
  -4.500  -0.1680   0.03551   0.02841  -0.0729   0.7666   0.0351
  -4.250  -0.1443   0.03250   0.02495  -0.0716   0.7655   0.0366
  -4.000  -0.1713   0.03364   0.02617  -0.0645   0.7596   0.0382
  -3.750  -0.1595   0.03327   0.02570  -0.0621   0.7564   0.0404
  -3.500  -0.1343   0.03256   0.02482  -0.0614   0.7546   0.0438
  -3.250  -0.1047   0.03188   0.02390  -0.0612   0.7532   0.0477
  -3.000  -0.0730   0.03058   0.02261  -0.0616   0.7521   0.0558
  -2.750  -0.0445   0.02993   0.02193  -0.0613   0.7509   0.0660
  -2.500  -0.0962   0.03157   0.02349  -0.0495   0.7421   0.0626
  -2.250  -0.0692   0.03106   0.02295  -0.0492   0.7401   0.0746
  -2.000  -0.0402   0.03041   0.02240  -0.0491   0.7388   0.0965
  -1.750  -0.0047   0.02969   0.02189  -0.0500   0.7378   0.1486
  -1.500   0.1171   0.02734   0.02240  -0.0681   0.7384   0.9357
  -1.250   0.2267   0.02809   0.02283  -0.0828   0.7386   0.9682
  -1.000   0.3127   0.02829   0.02279  -0.0938   0.7384   0.9817
  -0.750   0.4346   0.02807   0.02236  -0.1124   0.7389   1.0000
  -0.500   0.4115   0.02969   0.02399  -0.1062   0.7304   1.0000
  -0.250   0.4259   0.02987   0.02410  -0.1043   0.7274   1.0000
   0.000   0.4514   0.02972   0.02386  -0.1037   0.7257   1.0000
   0.250   0.4773   0.02962   0.02368  -0.1032   0.7245   1.0000
   0.500   0.4323   0.03136   0.02544  -0.0932   0.7137   1.0000
   0.750   0.4599   0.03128   0.02529  -0.0930   0.7121   1.0000
   1.000   0.4901   0.03117   0.02511  -0.0932   0.7110   1.0000
   1.250   0.4330   0.03249   0.02642  -0.0802   0.6996   1.0000
   1.500   0.4692   0.03238   0.02626  -0.0815   0.6983   1.0000
   1.750   0.5062   0.03231   0.02614  -0.0829   0.6973   1.0000
   2.000   0.4588   0.03342   0.02721  -0.0712   0.6860   1.0000
   2.250   0.4930   0.03332   0.02707  -0.0720   0.6846   1.0000
   2.500   0.5292   0.03323   0.02695  -0.0733   0.6836   1.0000
   2.750   0.5017   0.03433   0.02802  -0.0652   0.6726   1.0000
   3.000   0.5346   0.03421   0.02787  -0.0658   0.6712   1.0000
   3.250   0.5598   0.03430   0.02796  -0.0654   0.6685   1.0000
   3.500   0.5522   0.03527   0.02890  -0.0607   0.6594   1.0000
   3.750   0.5843   0.03512   0.02876  -0.0612   0.6579   1.0000
   4.000   0.6193   0.03487   0.02853  -0.0620   0.6569   1.0000
   4.250   0.6106   0.03601   0.02965  -0.0575   0.6462   1.0000
   4.500   0.6427   0.03578   0.02945  -0.0579   0.6446   1.0000
   4.750   0.6762   0.03553   0.02925  -0.0585   0.6436   1.0000
   5.000   0.7124   0.03508   0.02885  -0.0593   0.6427   1.0000
   5.250   0.7058   0.03624   0.03002  -0.0553   0.6313   1.0000
   5.500   0.7250   0.03656   0.03038  -0.0543   0.6269   1.0000
   5.750   0.7724   0.03551   0.02945  -0.0562   0.6290   1.0000
   6.000   0.7689   0.03677   0.03072  -0.0529   0.6179   1.0000
   6.250   0.8029   0.03627   0.03032  -0.0534   0.6167   1.0000
   6.500   0.8398   0.03550   0.02965  -0.0541   0.6159   1.0000
   6.750   0.8384   0.03675   0.03093  -0.0511   0.6045   1.0000
   7.000   0.8470   0.03764   0.03193  -0.0492   0.5959   1.0000
   7.250   0.8761   0.03724   0.03164  -0.0491   0.5927   1.0000
   7.500   0.9118   0.03634   0.03087  -0.0495   0.5912   1.0000
   7.750   0.9591   0.03407   0.02877  -0.0505   0.5903   1.0000
   8.000   1.0281   0.02815   0.02309  -0.0517   0.5839   1.0000
   8.250   1.1021   0.02034   0.01446  -0.0507   0.4407   1.0000
   8.500   1.0785   0.02270   0.01623  -0.0446   0.3639   1.0000
   8.750   1.0705   0.02459   0.01789  -0.0410   0.3195   1.0000
   9.000   1.0442   0.02777   0.02050  -0.0359   0.2379   1.0000
   9.250   1.0098   0.03178   0.02368  -0.0305   0.1261   1.0000
   9.500   0.9860   0.03548   0.02671  -0.0263   0.0403   1.0000
   9.750   0.9896   0.03729   0.02852  -0.0245   0.0318   1.0000
  10.000   0.9937   0.03916   0.03048  -0.0227   0.0268   1.0000
  10.250   0.9916   0.04160   0.03303  -0.0206   0.0237   1.0000
  10.500   0.9930   0.04380   0.03535  -0.0188   0.0224   1.0000
  10.750   1.0004   0.04548   0.03710  -0.0176   0.0193   1.0000
  11.000   1.0048   0.04746   0.03915  -0.0161   0.0182   1.0000
  11.250   1.0092   0.04942   0.04115  -0.0146   0.0172   1.0000
  11.500   1.0190   0.05087   0.04273  -0.0132   0.0176   1.0000
  11.750   1.0286   0.05231   0.04416  -0.0115   0.0164   1.0000
  12.000   1.0569   0.05256   0.04440  -0.0089   0.0156   1.0000
  12.250   1.0807   0.05336   0.04529  -0.0079   0.0158   1.0000
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