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FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-140/20 (fx78k140-il)
Reynolds number: 100,000
Max Cl/Cd: 26.19 at α=10°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k140-il-100000.txt
Download as CSV file: xf-fx78k140-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1111   0.11874   0.11390  -0.1055   0.9131   0.0704
 -11.750  -0.1192   0.11720   0.11243  -0.1091   0.9112   0.0740
 -11.500  -0.1235   0.11557   0.11084  -0.1122   0.9093   0.0745
 -11.250  -0.1252   0.11349   0.10879  -0.1147   0.9074   0.0748
 -11.000  -0.1026   0.10747   0.10275  -0.1128   0.9063   0.0773
 -10.750  -0.0918   0.10474   0.10000  -0.1132   0.9050   0.0794
 -10.500  -0.0957   0.10252   0.09783  -0.1154   0.9036   0.0872
 -10.250  -0.0925   0.10005   0.09536  -0.1169   0.9021   0.0873
 -10.000  -0.1103   0.09863   0.09402  -0.1212   0.9001   0.0886
  -9.750  -0.0837   0.09434   0.08970  -0.1175   0.8988   0.0972
  -9.500  -0.0919   0.09234   0.08777  -0.1197   0.8972   0.1009
  -9.250  -0.1034   0.09071   0.08619  -0.1219   0.8956   0.1019
  -9.000  -0.1305   0.08943   0.08500  -0.1245   0.8933   0.1026
  -8.750  -0.1053   0.08551   0.08107  -0.1211   0.8922   0.1065
  -8.500  -0.1081   0.08373   0.07933  -0.1202   0.8906   0.1120
  -8.250  -0.1272   0.08260   0.07828  -0.1195   0.8893   0.1133
  -8.000  -0.5054   0.12108   0.11771  -0.0258   1.0000   0.0740
  -7.750  -0.5315   0.11888   0.11555  -0.0264   1.0000   0.0743
  -7.500  -0.5565   0.11668   0.11339  -0.0255   1.0000   0.0744
  -7.250  -0.5808   0.11426   0.11094  -0.0257   1.0000   0.0747
  -7.000  -0.5983   0.11144   0.10803  -0.0259   1.0000   0.0749
  -6.750  -0.5863   0.10566   0.10242  -0.0212   1.0000   0.0769
  -6.500  -0.5893   0.10287   0.09963  -0.0193   1.0000   0.0780
  -6.250  -0.5942   0.09996   0.09671  -0.0178   1.0000   0.0796
  -6.000  -0.6003   0.09678   0.09351  -0.0169   1.0000   0.0820
  -5.750  -0.6052   0.09362   0.09029  -0.0168   1.0000   0.0840
  -5.500  -0.6184   0.09057   0.08661  -0.0209   0.9997   0.0890
  -5.250  -0.6030   0.08416   0.08048  -0.0209   0.9966   0.0910
  -4.750  -0.5648   0.07648   0.07247  -0.0260   0.9820   0.1058
  -4.500  -0.5480   0.07312   0.06892  -0.0274   0.9730   0.1198
  -4.250  -0.5288   0.07046   0.06588  -0.0290   0.9642   0.1326
  -4.000  -0.5077   0.06733   0.06285  -0.0293   0.9573   0.1394
  -3.750  -0.4928   0.06473   0.06006  -0.0291   0.9487   0.1516
  -3.500  -0.4705   0.06267   0.05766  -0.0301   0.9426   0.1764
  -3.000  -0.4089   0.04963   0.04235  -0.0261   0.9300   0.0716
  -2.750  -0.3906   0.04762   0.03991  -0.0242   0.9220   0.0710
  -2.500  -0.3623   0.04568   0.03740  -0.0235   0.9169   0.0707
  -2.250  -0.3409   0.04437   0.03570  -0.0222   0.9103   0.0692
  -2.000  -0.3113   0.04328   0.03410  -0.0217   0.9038   0.0730
  -1.500  -0.2618   0.04198   0.03245  -0.0208   0.8912   0.0865
  -1.250  -0.2264   0.04214   0.03255  -0.0222   0.8877   0.1006
  -1.000  -0.0738   0.03873   0.03304  -0.0501   0.8955   0.9882
  -0.750  -0.0451   0.04000   0.03376  -0.0507   0.8901   1.0000
  -0.500  -0.0276   0.04060   0.03406  -0.0496   0.8812   1.0000
  -0.250   0.0025   0.04177   0.03491  -0.0507   0.8749   1.0000
   0.000   0.0146   0.04209   0.03502  -0.0487   0.8649   1.0000
   0.250   0.0485   0.04366   0.03634  -0.0506   0.8604   1.0000
   0.500   0.0572   0.04374   0.03628  -0.0480   0.8498   1.0000
   0.750   0.0933   0.04561   0.03791  -0.0503   0.8462   1.0000
   1.000   0.0994   0.04552   0.03770  -0.0474   0.8353   1.0000
   1.250   0.1147   0.04635   0.03841  -0.0462   0.8287   1.0000
   1.500   0.1400   0.04733   0.03926  -0.0466   0.8214   1.0000
   1.750   0.1514   0.04799   0.03983  -0.0448   0.8137   1.0000
   2.000   0.1819   0.04928   0.04098  -0.0460   0.8073   1.0000
   2.250   0.1897   0.04980   0.04141  -0.0438   0.7987   1.0000
   2.500   0.2220   0.05128   0.04279  -0.0453   0.7934   1.0000
   2.750   0.2272   0.05174   0.04321  -0.0429   0.7847   1.0000
   3.000   0.2622   0.05334   0.04473  -0.0447   0.7794   1.0000
   3.250   0.2660   0.05373   0.04508  -0.0422   0.7699   1.0000
   3.500   0.3040   0.05557   0.04686  -0.0444   0.7654   1.0000
   3.750   0.3056   0.05581   0.04708  -0.0417   0.7551   1.0000
   4.000   0.3473   0.05793   0.04917  -0.0443   0.7511   1.0000
   4.250   0.3511   0.05804   0.04926  -0.0418   0.7395   1.0000
   4.500   0.3628   0.05876   0.04998  -0.0405   0.7288   1.0000
   4.750   0.3925   0.06017   0.05138  -0.0414   0.7223   1.0000
   5.000   0.4461   0.05806   0.04924  -0.0420   0.6859   1.0000
   5.250   0.4647   0.05858   0.04978  -0.0412   0.6748   1.0000
   5.500   0.4907   0.05910   0.05031  -0.0412   0.6656   1.0000
   5.750   0.5193   0.05960   0.05086  -0.0415   0.6582   1.0000
   6.000   0.5306   0.06045   0.05173  -0.0403   0.6483   1.0000
   6.250   0.5707   0.06076   0.05215  -0.0416   0.6434   1.0000
   6.500   0.5785   0.06157   0.05300  -0.0400   0.6324   1.0000
   6.750   0.5953   0.06236   0.05385  -0.0393   0.6237   1.0000
   7.000   0.6247   0.06282   0.05439  -0.0397   0.6178   1.0000
   7.250   0.6343   0.06394   0.05562  -0.0385   0.6082   1.0000
   7.500   0.6687   0.06418   0.05598  -0.0392   0.6036   1.0000
   7.750   0.6786   0.06515   0.05704  -0.0380   0.5928   1.0000
   8.000   0.7188   0.06498   0.05702  -0.0390   0.5891   1.0000
   8.250   0.7247   0.06626   0.05840  -0.0376   0.5778   1.0000
   9.750   1.0108   0.04333   0.03711  -0.0318   0.5046   1.0000
  10.000   1.0202   0.03895   0.03112  -0.0236   0.2643   1.0000
  10.250   0.9884   0.04335   0.03438  -0.0193   0.1299   1.0000
  10.500   0.9724   0.04688   0.03720  -0.0161   0.0686   1.0000
  10.750   0.9688   0.04957   0.03982  -0.0138   0.0559   1.0000
  11.000   0.9707   0.05182   0.04215  -0.0121   0.0479   1.0000
  11.250   0.9697   0.05428   0.04461  -0.0102   0.0428   1.0000
  11.500   0.9775   0.05593   0.04636  -0.0087   0.0402   1.0000
  11.750   0.9897   0.05712   0.04766  -0.0069   0.0385   1.0000
  12.000   1.0121   0.05757   0.04801  -0.0047   0.0351   1.0000
  12.250   1.1062   0.05698   0.04731  -0.0043   0.0329   1.0000
  12.500   1.1637   0.05993   0.05056  -0.0051   0.0329   1.0000
  12.750   1.1484   0.06158   0.05256  -0.0023   0.0315   1.0000
  13.000   1.1653   0.06493   0.05627  -0.0012   0.0315   1.0000
  13.250   1.1831   0.06928   0.06093  -0.0004   0.0324   1.0000
  13.500   1.2020   0.07297   0.06488   0.0003   0.0335   1.0000
  13.750   1.1876   0.07516   0.06749   0.0031   0.0350   1.0000
  14.000   1.1595   0.07939   0.07225   0.0057   0.0367   1.0000
  14.250   1.1442   0.08347   0.07663   0.0069   0.0374   1.0000
  14.500   1.1270   0.08825   0.08171   0.0079   0.0391   1.0000
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