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FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 61-140 AIRFOIL (fx61140-il)
Reynolds number: 50,000
Max Cl/Cd: 31.17 at α=9.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61140-il-50000-n5.txt
Download as CSV file: xf-fx61140-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4062   0.10233   0.09541  -0.0438   1.0000   0.0407
 -10.000  -0.4103   0.09724   0.09040  -0.0460   1.0000   0.0404
  -9.750  -0.4159   0.09185   0.08508  -0.0485   1.0000   0.0399
  -9.500  -0.4247   0.08639   0.07969  -0.0511   1.0000   0.0392
  -9.250  -0.4384   0.08114   0.07450  -0.0537   1.0000   0.0386
  -9.000  -0.4555   0.07647   0.06986  -0.0554   1.0000   0.0377
  -8.750  -0.4772   0.07246   0.06588  -0.0558   1.0000   0.0372
  -8.500  -0.5004   0.06923   0.06266  -0.0549   1.0000   0.0364
  -8.250  -0.5179   0.06571   0.05909  -0.0546   1.0000   0.0360
  -8.000  -0.5305   0.06245   0.05572  -0.0537   1.0000   0.0360
  -7.750  -0.5387   0.05927   0.05238  -0.0527   1.0000   0.0362
  -7.500  -0.5429   0.05613   0.04904  -0.0516   1.0000   0.0364
  -7.250  -0.5429   0.05302   0.04568  -0.0506   1.0000   0.0366
  -7.000  -0.5392   0.04991   0.04228  -0.0496   1.0000   0.0368
  -6.750  -0.5316   0.04690   0.03893  -0.0487   1.0000   0.0369
  -6.500  -0.5206   0.04408   0.03577  -0.0478   1.0000   0.0371
  -6.250  -0.5068   0.04148   0.03282  -0.0469   1.0000   0.0376
  -6.000  -0.4912   0.03922   0.03017  -0.0458   1.0000   0.0382
  -5.750  -0.4745   0.03725   0.02789  -0.0445   1.0000   0.0394
  -5.500  -0.4417   0.03541   0.02557  -0.0456   0.9949   0.0428
  -5.250  -0.4058   0.03338   0.02350  -0.0470   0.9865   0.0469
  -5.000  -0.3705   0.03200   0.02198  -0.0473   0.9769   0.0508
  -4.750  -0.3362   0.03080   0.02061  -0.0478   0.9661   0.0582
  -4.500  -0.3025   0.02949   0.01921  -0.0492   0.9540   0.0679
  -4.250  -0.2683   0.02790   0.01760  -0.0515   0.9415   0.0853
  -3.750  -0.2178   0.02441   0.01712  -0.0515   0.9162   0.5550
  -3.500  -0.1987   0.02737   0.01997  -0.0444   0.9007   0.6598
  -3.250  -0.1797   0.02928   0.02168  -0.0376   0.8875   0.7058
  -3.000  -0.1446   0.02918   0.02117  -0.0381   0.8764   0.7211
  -2.750  -0.1117   0.02893   0.02058  -0.0387   0.8636   0.7323
  -2.500  -0.0775   0.02860   0.01994  -0.0400   0.8510   0.7429
  -2.250  -0.0425   0.02825   0.01929  -0.0416   0.8385   0.7531
  -2.000  -0.0095   0.02794   0.01871  -0.0422   0.8263   0.7602
  -1.750   0.0251   0.02758   0.01809  -0.0439   0.8141   0.7690
  -1.500   0.0592   0.02726   0.01754  -0.0448   0.8027   0.7754
  -1.250   0.0921   0.02696   0.01699  -0.0462   0.7904   0.7831
  -1.000   0.1210   0.02672   0.01658  -0.0463   0.7775   0.7891
  -0.750   0.1508   0.02652   0.01620  -0.0473   0.7648   0.7964
  -0.500   0.1789   0.02633   0.01585  -0.0472   0.7527   0.8018
  -0.250   0.2087   0.02618   0.01554  -0.0481   0.7410   0.8084
   0.000   0.2386   0.02601   0.01522  -0.0485   0.7303   0.8137
   0.250   0.2662   0.02590   0.01500  -0.0488   0.7192   0.8193
   0.500   0.2923   0.02587   0.01486  -0.0491   0.7075   0.8252
   0.750   0.3182   0.02581   0.01473  -0.0489   0.6970   0.8301
   1.000   0.3483   0.02575   0.01457  -0.0497   0.6877   0.8355
   1.250   0.3734   0.02577   0.01454  -0.0496   0.6772   0.8406
   1.500   0.3979   0.02581   0.01455  -0.0494   0.6671   0.8456
   1.750   0.4276   0.02584   0.01450  -0.0502   0.6584   0.8511
   2.000   0.4515   0.02591   0.01457  -0.0499   0.6487   0.8558
   2.250   0.4760   0.02602   0.01470  -0.0497   0.6394   0.8609
   2.500   0.5070   0.02609   0.01471  -0.0507   0.6315   0.8661
   2.750   0.5274   0.02627   0.01495  -0.0499   0.6218   0.8708
   3.000   0.5542   0.02640   0.01512  -0.0500   0.6137   0.8758
   3.250   0.5801   0.02660   0.01535  -0.0503   0.6051   0.8809
   3.500   0.6027   0.02682   0.01564  -0.0498   0.5967   0.8856
   3.750   0.6309   0.02698   0.01582  -0.0502   0.5893   0.8906
   4.000   0.6522   0.02735   0.01633  -0.0498   0.5805   0.8959
   4.250   0.6814   0.02746   0.01648  -0.0502   0.5739   0.9006
   4.500   0.7012   0.02795   0.01710  -0.0497   0.5647   0.9063
   4.750   0.7295   0.02812   0.01734  -0.0500   0.5581   0.9113
   5.000   0.7490   0.02861   0.01803  -0.0494   0.5492   0.9172
   5.250   0.7750   0.02894   0.01847  -0.0496   0.5419   0.9228
   5.500   0.7974   0.02937   0.01906  -0.0493   0.5338   0.9290
   5.750   0.8212   0.02986   0.01971  -0.0493   0.5260   0.9354
   6.000   0.8469   0.03026   0.02031  -0.0495   0.5184   0.9419
   6.250   0.8684   0.03092   0.02118  -0.0494   0.5102   0.9495
   6.500   0.8984   0.03127   0.02169  -0.0502   0.5030   0.9570
   6.750   0.9190   0.03216   0.02285  -0.0503   0.4940   0.9670
   7.000   0.9561   0.03236   0.02325  -0.0520   0.4872   0.9786
   7.250   0.9732   0.03351   0.02470  -0.0520   0.4770   1.0000
   7.500   0.9989   0.03431   0.02572  -0.0526   0.4684   1.0000
   7.750   1.0288   0.03486   0.02649  -0.0536   0.4599   1.0000
   8.000   1.0464   0.03611   0.02804  -0.0536   0.4497   1.0000
   8.250   1.0733   0.03675   0.02892  -0.0541   0.4400   1.0000
   8.500   1.1083   0.03672   0.02917  -0.0551   0.4297   1.0000
   8.750   1.1280   0.03740   0.03014  -0.0547   0.4165   1.0000
   9.000   1.1513   0.03763   0.03061  -0.0544   0.4020   1.0000
   9.250   1.1688   0.03790   0.03113  -0.0535   0.3850   1.0000
   9.500   1.1783   0.03855   0.03203  -0.0518   0.3664   1.0000
   9.750   1.1927   0.03826   0.03184  -0.0500   0.3441   1.0000
  10.000   1.1893   0.03979   0.03358  -0.0478   0.3223   1.0000
  10.250   1.1891   0.04120   0.03510  -0.0462   0.2967   1.0000
  10.500   1.1869   0.04324   0.03722  -0.0452   0.2695   1.0000
  10.750   1.1823   0.04595   0.04005  -0.0449   0.2403   1.0000
  11.000   1.1758   0.04921   0.04325  -0.0449   0.2081   1.0000
  11.250   1.1661   0.05315   0.04700  -0.0454   0.1775   1.0000
  11.500   1.1538   0.05778   0.05146  -0.0463   0.1515   1.0000
  11.750   1.1411   0.06274   0.05626  -0.0475   0.1311   1.0000
  12.000   1.1290   0.06782   0.06121  -0.0489   0.1151   1.0000
  12.250   1.1190   0.07280   0.06610  -0.0502   0.1022   1.0000
  12.500   1.1113   0.07753   0.07077  -0.0514   0.0920   1.0000
  12.750   1.1047   0.08217   0.07532  -0.0526   0.0831   1.0000
  13.000   1.1003   0.08672   0.07990  -0.0540   0.0740   1.0000
  13.250   1.0982   0.09103   0.08429  -0.0551   0.0660   1.0000
  13.500   1.0966   0.09516   0.08831  -0.0562   0.0596   1.0000
  13.750   1.0952   0.09977   0.09314  -0.0579   0.0525   1.0000
  14.000   1.0928   0.10429   0.09762  -0.0597   0.0471   1.0000
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