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FX 61-140 AIRFOIL (fx61140-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 61-140 AIRFOIL (fx61140-il)
Reynolds number: 100,000
Max Cl/Cd: 52.04 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61140-il-100000-n5.txt
Download as CSV file: xf-fx61140-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.2950   0.11615   0.11140  -0.0380   1.0000   0.0276
 -11.500  -0.2973   0.11187   0.10715  -0.0391   1.0000   0.0261
 -11.000  -0.4090   0.10771   0.10266  -0.0410   1.0000   0.0222
 -10.750  -0.4084   0.10405   0.09904  -0.0413   1.0000   0.0217
 -10.500  -0.4106   0.09934   0.09438  -0.0429   1.0000   0.0214
 -10.250  -0.4134   0.09461   0.08970  -0.0447   1.0000   0.0211
 -10.000  -0.4185   0.08911   0.08426  -0.0470   1.0000   0.0208
  -9.750  -0.4269   0.08268   0.07788  -0.0505   1.0000   0.0204
  -9.500  -0.4403   0.07663   0.07184  -0.0539   1.0000   0.0200
  -9.250  -0.4572   0.07144   0.06664  -0.0563   1.0000   0.0196
  -9.000  -0.4764   0.06721   0.06239  -0.0573   1.0000   0.0194
  -8.750  -0.4996   0.06372   0.05887  -0.0567   1.0000   0.0193
  -8.500  -0.5219   0.06122   0.05636  -0.0545   1.0000   0.0190
  -8.250  -0.5390   0.05805   0.05311  -0.0535   1.0000   0.0190
  -8.000  -0.5514   0.05489   0.04981  -0.0520   1.0000   0.0189
  -7.750  -0.5597   0.05170   0.04643  -0.0505   1.0000   0.0188
  -7.500  -0.5633   0.04854   0.04303  -0.0490   1.0000   0.0186
  -7.250  -0.5505   0.04437   0.03846  -0.0506   0.9968   0.0185
  -7.000  -0.5215   0.03972   0.03324  -0.0544   0.9895   0.0185
  -6.750  -0.4893   0.03585   0.02882  -0.0575   0.9825   0.0188
  -6.500  -0.4561   0.03266   0.02515  -0.0598   0.9750   0.0192
  -6.250  -0.4232   0.03005   0.02208  -0.0613   0.9668   0.0201
  -6.000  -0.3861   0.02835   0.01997  -0.0632   0.9595   0.0221
  -5.750  -0.3569   0.02615   0.01775  -0.0640   0.9496   0.0244
  -5.500  -0.3254   0.02460   0.01611  -0.0648   0.9397   0.0261
  -5.250  -0.2917   0.02314   0.01457  -0.0659   0.9309   0.0284
  -5.000  -0.2590   0.02191   0.01324  -0.0670   0.9202   0.0324
  -4.750  -0.2261   0.02064   0.01193  -0.0686   0.9084   0.0386
  -4.500  -0.1896   0.01947   0.01066  -0.0708   0.8967   0.0482
  -4.250  -0.1503   0.01821   0.00946  -0.0737   0.8854   0.0758
  -4.000  -0.1065   0.01520   0.00850  -0.0801   0.8754   0.4550
  -3.750  -0.0793   0.01592   0.00960  -0.0778   0.8599   0.5877
  -3.500  -0.0492   0.01722   0.01075  -0.0758   0.8437   0.6418
  -3.250  -0.0194   0.01795   0.01128  -0.0744   0.8270   0.6596
  -3.000   0.0175   0.01797   0.01102  -0.0759   0.8101   0.6701
  -2.750   0.0501   0.01808   0.01088  -0.0763   0.7932   0.6764
  -2.500   0.0855   0.01803   0.01055  -0.0778   0.7763   0.6844
  -2.250   0.1153   0.01810   0.01042  -0.0778   0.7597   0.6894
  -2.000   0.1494   0.01800   0.01008  -0.0795   0.7433   0.6974
  -1.750   0.1766   0.01808   0.00999  -0.0790   0.7280   0.7011
  -1.500   0.2062   0.01809   0.00982  -0.0794   0.7135   0.7066
  -1.250   0.2375   0.01804   0.00959  -0.0804   0.6998   0.7125
  -1.000   0.2641   0.01810   0.00951  -0.0800   0.6871   0.7163
  -0.750   0.2932   0.01812   0.00938  -0.0804   0.6751   0.7215
  -0.500   0.3229   0.01811   0.00924  -0.0811   0.6630   0.7268
  -0.250   0.3485   0.01817   0.00921  -0.0806   0.6519   0.7303
   0.000   0.3768   0.01821   0.00914  -0.0809   0.6417   0.7348
   0.250   0.4080   0.01822   0.00903  -0.0820   0.6317   0.7401
   0.500   0.4330   0.01828   0.00905  -0.0814   0.6215   0.7432
   0.750   0.4601   0.01834   0.00905  -0.0814   0.6125   0.7469
   1.000   0.4900   0.01840   0.00902  -0.0822   0.6035   0.7515
   1.250   0.5180   0.01846   0.00905  -0.0825   0.5942   0.7553
   1.500   0.5442   0.01855   0.00910  -0.0822   0.5864   0.7584
   1.750   0.5713   0.01863   0.00917  -0.0823   0.5776   0.7621
   2.000   0.6016   0.01873   0.00923  -0.0832   0.5697   0.7666
   2.250   0.6285   0.01883   0.00935  -0.0832   0.5619   0.7698
   2.500   0.6543   0.01895   0.00948  -0.0830   0.5545   0.7730
   2.750   0.6820   0.01907   0.00961  -0.0832   0.5471   0.7766
   3.000   0.7118   0.01922   0.00977  -0.0840   0.5396   0.7808
   3.250   0.7385   0.01935   0.00995  -0.0840   0.5325   0.7838
   3.500   0.7640   0.01950   0.01016  -0.0837   0.5253   0.7869
   3.750   0.7912   0.01966   0.01035  -0.0838   0.5182   0.7902
   4.000   0.8198   0.01985   0.01061  -0.0844   0.5109   0.7940
   4.250   0.8475   0.02003   0.01087  -0.0846   0.5039   0.7972
   4.500   0.8726   0.02022   0.01115  -0.0843   0.4969   0.8001
   4.750   0.8990   0.02042   0.01143  -0.0842   0.4900   0.8033
   5.000   0.9269   0.02066   0.01180  -0.0846   0.4832   0.8069
   5.250   0.9557   0.02092   0.01216  -0.0852   0.4760   0.8104
   5.500   0.9803   0.02114   0.01250  -0.0847   0.4695   0.8131
   5.750   1.0056   0.02138   0.01289  -0.0845   0.4621   0.8162
   6.000   1.0323   0.02165   0.01328  -0.0846   0.4551   0.8197
   6.250   1.0601   0.02194   0.01375  -0.0850   0.4471   0.8233
   6.500   1.0847   0.02222   0.01419  -0.0846   0.4395   0.8262
   6.750   1.1093   0.02248   0.01461  -0.0842   0.4319   0.8294
   7.000   1.1337   0.02278   0.01510  -0.0838   0.4227   0.8329
   7.250   1.1591   0.02301   0.01547  -0.0837   0.4119   0.8363
   7.500   1.1821   0.02319   0.01583  -0.0830   0.3991   0.8396
   7.750   1.2017   0.02335   0.01617  -0.0817   0.3838   0.8429
   8.000   1.2204   0.02353   0.01650  -0.0804   0.3637   0.8467
   8.250   1.2390   0.02381   0.01686  -0.0791   0.3395   0.8504
   8.500   1.2552   0.02422   0.01734  -0.0775   0.3138   0.8539
   8.750   1.2694   0.02476   0.01795  -0.0756   0.2883   0.8576
   9.000   1.2817   0.02553   0.01875  -0.0737   0.2539   0.8619
   9.250   1.2875   0.02680   0.01983  -0.0712   0.2066   0.8663
   9.500   1.2820   0.02841   0.02120  -0.0671   0.1608   0.8704
   9.750   1.2736   0.03060   0.02318  -0.0633   0.1197   0.8753
  10.000   1.2652   0.03306   0.02546  -0.0603   0.0892   0.8805
  10.250   1.2557   0.03551   0.02784  -0.0573   0.0691   0.8858
  10.500   1.2482   0.03822   0.03053  -0.0555   0.0541   0.8916
  10.750   1.2410   0.04105   0.03341  -0.0540   0.0440   0.8973
  11.000   1.2331   0.04422   0.03661  -0.0532   0.0361   0.9036
  11.250   1.2269   0.04746   0.03996  -0.0527   0.0302   0.9107
  11.500   1.2177   0.05114   0.04375  -0.0526   0.0266   0.9197
  11.750   1.2103   0.05468   0.04750  -0.0524   0.0235   0.9323
  12.000   1.2001   0.05856   0.05154  -0.0525   0.0214   0.9602
  12.250   1.1903   0.06333   0.05644  -0.0540   0.0196   1.0000
  12.500   1.1844   0.06804   0.06131  -0.0556   0.0181   1.0000
  12.750   1.1803   0.07257   0.06603  -0.0571   0.0167   1.0000
  13.000   1.1770   0.07706   0.07068  -0.0587   0.0156   1.0000
  13.250   1.1743   0.08154   0.07529  -0.0604   0.0147   1.0000
  13.500   1.1719   0.08602   0.07989  -0.0621   0.0140   1.0000
  13.750   1.1699   0.09047   0.08446  -0.0637   0.0134   1.0000
  14.000   1.1683   0.09478   0.08885  -0.0651   0.0128   1.0000
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