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FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 61-140 AIRFOIL (fx61140-il)
Reynolds number: 200,000
Max Cl/Cd: 70.62 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61140-il-200000-n5.txt
Download as CSV file: xf-fx61140-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-140 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4289   0.08911   0.08565  -0.0434   1.0000   0.0089
 -10.000  -0.4394   0.08177   0.07835  -0.0471   1.0000   0.0087
  -9.750  -0.4576   0.07249   0.06906  -0.0531   1.0000   0.0085
  -9.500  -0.4798   0.06587   0.06238  -0.0566   1.0000   0.0083
  -9.250  -0.5024   0.06103   0.05747  -0.0579   1.0000   0.0081
  -9.000  -0.5252   0.05745   0.05384  -0.0571   1.0000   0.0080
  -8.750  -0.5520   0.05486   0.05119  -0.0542   1.0000   0.0081
  -8.500  -0.5722   0.05195   0.04820  -0.0522   1.0000   0.0080
  -8.250  -0.5690   0.04604   0.04192  -0.0563   0.9951   0.0079
  -8.000  -0.5536   0.04001   0.03538  -0.0605   0.9875   0.0079
  -7.750  -0.5328   0.03526   0.03013  -0.0633   0.9800   0.0080
  -7.500  -0.5063   0.03128   0.02564  -0.0658   0.9735   0.0083
  -7.250  -0.4810   0.02825   0.02218  -0.0668   0.9651   0.0086
  -7.000  -0.4496   0.02603   0.01953  -0.0683   0.9588   0.0098
  -6.750  -0.4224   0.02410   0.01737  -0.0691   0.9495   0.0107
  -6.500  -0.3932   0.02287   0.01604  -0.0701   0.9403   0.0116
  -6.250  -0.3609   0.02133   0.01430  -0.0712   0.9328   0.0124
  -6.000  -0.3311   0.01998   0.01283  -0.0718   0.9219   0.0131
  -5.750  -0.2980   0.01873   0.01145  -0.0730   0.9117   0.0142
  -5.500  -0.2610   0.01741   0.01005  -0.0755   0.9015   0.0162
  -5.250  -0.2185   0.01645   0.00904  -0.0791   0.8902   0.0194
  -5.000  -0.1733   0.01545   0.00785  -0.0833   0.8762   0.0221
  -4.750  -0.1277   0.01448   0.00678  -0.0877   0.8587   0.0297
  -4.500  -0.0830   0.01371   0.00590  -0.0918   0.8383   0.0446
  -4.250  -0.0411   0.01243   0.00504  -0.0963   0.8162   0.1518
  -4.000   0.0019   0.01059   0.00432  -0.1021   0.7931   0.4436
  -3.750   0.0324   0.01054   0.00457  -0.1024   0.7710   0.5567
  -3.500   0.0597   0.01095   0.00495  -0.1016   0.7503   0.6070
  -3.250   0.0863   0.01140   0.00525  -0.1007   0.7311   0.6310
  -3.000   0.1147   0.01159   0.00523  -0.1006   0.7129   0.6418
  -2.750   0.1417   0.01178   0.00525  -0.1002   0.6963   0.6481
  -2.500   0.1706   0.01188   0.00516  -0.1005   0.6809   0.6553
  -2.250   0.1971   0.01204   0.00518  -0.1000   0.6667   0.6594
  -2.000   0.2256   0.01213   0.00511  -0.1002   0.6534   0.6650
  -1.750   0.2540   0.01222   0.00505  -0.1003   0.6409   0.6699
  -1.500   0.2807   0.01236   0.00508  -0.1000   0.6295   0.6733
  -1.250   0.3087   0.01245   0.00505  -0.1000   0.6184   0.6776
  -1.000   0.3389   0.01249   0.00496  -0.1008   0.6076   0.6829
  -0.750   0.3653   0.01262   0.00501  -0.1004   0.5977   0.6855
  -0.500   0.3924   0.01274   0.00505  -0.1002   0.5884   0.6887
  -0.250   0.4210   0.01282   0.00505  -0.1005   0.5788   0.6929
   0.000   0.4508   0.01289   0.00502  -0.1011   0.5700   0.6974
   0.250   0.4774   0.01300   0.00509  -0.1008   0.5616   0.6997
   0.500   0.5047   0.01310   0.00516  -0.1007   0.5533   0.7025
   0.750   0.5329   0.01321   0.00520  -0.1009   0.5457   0.7057
   1.000   0.5627   0.01327   0.00522  -0.1016   0.5379   0.7097
   1.250   0.5908   0.01339   0.00529  -0.1017   0.5311   0.7125
   1.500   0.6179   0.01349   0.00540  -0.1016   0.5240   0.7147
   1.750   0.6453   0.01361   0.00550  -0.1016   0.5173   0.7173
   2.000   0.6737   0.01371   0.00562  -0.1019   0.5104   0.7204
   2.250   0.7031   0.01383   0.00569  -0.1025   0.5038   0.7241
   2.500   0.7311   0.01394   0.00582  -0.1026   0.4971   0.7267
   2.750   0.7578   0.01407   0.00597  -0.1024   0.4903   0.7289
   3.000   0.7851   0.01421   0.00614  -0.1024   0.4841   0.7313
   3.250   0.8130   0.01434   0.00630  -0.1026   0.4773   0.7342
   3.500   0.8417   0.01449   0.00645  -0.1030   0.4713   0.7375
   3.750   0.8703   0.01461   0.00665  -0.1034   0.4644   0.7402
   4.000   0.8968   0.01478   0.00684  -0.1032   0.4588   0.7421
   4.250   0.9238   0.01492   0.00708  -0.1032   0.4524   0.7443
   4.500   0.9509   0.01510   0.00730  -0.1032   0.4461   0.7469
   4.750   0.9787   0.01526   0.00756  -0.1034   0.4397   0.7497
   5.000   1.0070   0.01544   0.00779  -0.1037   0.4330   0.7526
   5.250   1.0340   0.01563   0.00805  -0.1037   0.4261   0.7549
   5.500   1.0599   0.01581   0.00833  -0.1034   0.4188   0.7569
   5.750   1.0862   0.01601   0.00865  -0.1033   0.4121   0.7592
   6.000   1.1125   0.01621   0.00895  -0.1032   0.4041   0.7616
   6.250   1.1387   0.01641   0.00924  -0.1031   0.3936   0.7645
   6.500   1.1647   0.01663   0.00951  -0.1030   0.3803   0.7674
   6.750   1.1877   0.01684   0.00977  -0.1022   0.3621   0.7694
   7.000   1.2097   0.01713   0.01008  -0.1013   0.3404   0.7716
   7.250   1.2310   0.01751   0.01047  -0.1004   0.3151   0.7740
   7.500   1.2504   0.01807   0.01093  -0.0993   0.2783   0.7767
   7.750   1.2648   0.01909   0.01164  -0.0977   0.2199   0.7793
   8.000   1.2739   0.02066   0.01276  -0.0955   0.1495   0.7820
   8.250   1.2837   0.02200   0.01390  -0.0932   0.1071   0.7841
   8.500   1.2936   0.02328   0.01505  -0.0909   0.0759   0.7864
   8.750   1.3009   0.02467   0.01631  -0.0884   0.0498   0.7889
   9.000   1.3077   0.02587   0.01748  -0.0857   0.0344   0.7915
   9.250   1.3151   0.02710   0.01876  -0.0832   0.0250   0.7943
   9.500   1.3209   0.02843   0.02015  -0.0806   0.0184   0.7970
   9.750   1.3239   0.02992   0.02173  -0.0779   0.0131   0.7995
  10.000   1.3281   0.03145   0.02338  -0.0756   0.0101   0.8022
  10.250   1.3291   0.03334   0.02535  -0.0735   0.0082   0.8049
  10.500   1.3332   0.03516   0.02733  -0.0720   0.0071   0.8077
  10.750   1.3362   0.03722   0.02952  -0.0708   0.0064   0.8105
  11.000   1.3363   0.03957   0.03202  -0.0696   0.0058   0.8130
  11.250   1.3349   0.04231   0.03491  -0.0688   0.0055   0.8158
  11.500   1.3335   0.04530   0.03807  -0.0684   0.0053   0.8187
  11.750   1.3324   0.04847   0.04141  -0.0685   0.0051   0.8216
  12.000   1.3309   0.05186   0.04497  -0.0687   0.0049   0.8243
  12.250   1.3281   0.05541   0.04870  -0.0691   0.0048   0.8265
  12.500   1.3244   0.05922   0.05268  -0.0696   0.0047   0.8289
  12.750   1.3204   0.06319   0.05682  -0.0703   0.0046   0.8315
  13.000   1.3167   0.06727   0.06109  -0.0712   0.0045   0.8344
  13.250   1.3123   0.07155   0.06553  -0.0723   0.0044   0.8372
  13.500   1.3076   0.07591   0.07004  -0.0735   0.0043   0.8397
  13.750   1.3032   0.08032   0.07461  -0.0747   0.0042   0.8422
  14.000   1.2989   0.08485   0.07929  -0.0760   0.0041   0.8449
  14.250   1.2949   0.08947   0.08406  -0.0775   0.0041   0.8476
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