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R140 (original) (r140-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: R140 (original) (r140-il)
Reynolds number: 50,000
Max Cl/Cd: 28.7 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-r140-il-50000-n5.txt
Download as CSV file: xf-r140-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: R140 (original)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5503   0.09802   0.09125  -0.0328   1.0000   0.0222
 -10.500  -0.5583   0.09165   0.08492  -0.0365   1.0000   0.0219
 -10.250  -0.5692   0.08579   0.07909  -0.0400   1.0000   0.0216
 -10.000  -0.5817   0.08069   0.07398  -0.0428   1.0000   0.0212
  -9.750  -0.6000   0.07561   0.06886  -0.0448   1.0000   0.0211
  -9.500  -0.6151   0.07178   0.06496  -0.0453   1.0000   0.0209
  -9.250  -0.6334   0.06816   0.06125  -0.0442   1.0000   0.0208
  -9.000  -0.6495   0.06519   0.05818  -0.0418   1.0000   0.0206
  -8.750  -0.6625   0.06223   0.05507  -0.0390   1.0000   0.0205
  -8.500  -0.6724   0.05909   0.05174  -0.0362   1.0000   0.0204
  -8.250  -0.6791   0.05598   0.04838  -0.0331   1.0000   0.0203
  -8.000  -0.6829   0.05289   0.04502  -0.0300   1.0000   0.0203
  -7.750  -0.6832   0.04991   0.04172  -0.0268   1.0000   0.0201
  -7.500  -0.6807   0.04693   0.03839  -0.0237   1.0000   0.0205
  -7.250  -0.6741   0.04411   0.03520  -0.0207   1.0000   0.0209
  -7.000  -0.6633   0.04135   0.03189  -0.0181   1.0000   0.0214
  -6.750  -0.6481   0.03873   0.02884  -0.0159   1.0000   0.0230
  -6.500  -0.6278   0.03631   0.02601  -0.0142   1.0000   0.0242
  -6.250  -0.6085   0.03424   0.02380  -0.0127   1.0000   0.0265
  -6.000  -0.5874   0.03252   0.02192  -0.0112   1.0000   0.0295
  -5.750  -0.5659   0.03091   0.02008  -0.0095   1.0000   0.0321
  -5.500  -0.5503   0.02953   0.01842  -0.0068   1.0000   0.0359
  -5.250  -0.5417   0.02818   0.01705  -0.0038   1.0000   0.0450
  -5.000  -0.5357   0.02676   0.01550  -0.0001   1.0000   0.0558
  -4.750  -0.5302   0.02542   0.01425   0.0034   1.0000   0.0724
  -4.500  -0.5229   0.02426   0.01319   0.0065   1.0000   0.1084
  -4.250  -0.5181   0.02269   0.01206   0.0095   1.0000   0.1933
  -4.000  -0.5230   0.02073   0.01158   0.0145   1.0000   0.4349
  -3.750  -0.5172   0.02041   0.01172   0.0193   1.0000   0.5785
  -3.500  -0.5111   0.02042   0.01187   0.0241   1.0000   0.6658
  -3.250  -0.4860   0.02133   0.01288   0.0278   0.9960   0.7605
  -3.000  -0.4477   0.02230   0.01360   0.0281   0.9885   0.8128
  -2.750  -0.4017   0.02290   0.01385   0.0256   0.9820   0.8389
  -2.500  -0.3550   0.02317   0.01378   0.0219   0.9747   0.8539
  -2.250  -0.3099   0.02331   0.01360   0.0182   0.9661   0.8668
  -2.000  -0.2617   0.02339   0.01331   0.0136   0.9584   0.8772
  -1.750  -0.2122   0.02344   0.01312   0.0088   0.9500   0.8847
  -1.500  -0.1675   0.02343   0.01290   0.0047   0.9411   0.8938
  -1.250  -0.1160   0.02344   0.01267  -0.0007   0.9342   0.9008
  -1.000  -0.0720   0.02342   0.01256  -0.0046   0.9251   0.9093
  -0.750  -0.0257   0.02340   0.01243  -0.0090   0.9180   0.9187
  -0.500   0.0237   0.02337   0.01235  -0.0140   0.9106   0.9262
  -0.250   0.0695   0.02332   0.01224  -0.0184   0.9033   0.9352
   0.000   0.1155   0.02323   0.01214  -0.0227   0.8958   0.9435
   0.250   0.1591   0.02315   0.01209  -0.0267   0.8872   0.9514
   0.500   0.2030   0.02304   0.01203  -0.0306   0.8800   0.9599
   0.750   0.2445   0.02297   0.01203  -0.0343   0.8698   0.9681
   1.000   0.2859   0.02290   0.01206  -0.0379   0.8605   0.9773
   1.250   0.3312   0.02277   0.01215  -0.0422   0.8531   0.9861
   1.500   0.3734   0.02268   0.01222  -0.0460   0.8435   0.9955
   1.750   0.4071   0.02261   0.01229  -0.0480   0.8341   1.0000
   2.000   0.4320   0.02257   0.01238  -0.0480   0.8250   1.0000
   2.250   0.4528   0.02265   0.01259  -0.0473   0.8150   1.0000
   2.500   0.4708   0.02287   0.01305  -0.0461   0.8046   1.0000
   2.750   0.4878   0.02313   0.01348  -0.0448   0.7943   1.0000
   3.000   0.5061   0.02339   0.01393  -0.0436   0.7847   1.0000
   3.250   0.5250   0.02361   0.01437  -0.0422   0.7742   1.0000
   3.500   0.5450   0.02366   0.01465  -0.0406   0.7609   1.0000
   3.750   0.5656   0.02355   0.01478  -0.0386   0.7441   1.0000
   4.000   0.5877   0.02295   0.01441  -0.0355   0.7158   1.0000
   4.250   0.6060   0.02222   0.01381  -0.0313   0.6767   1.0000
   4.500   0.6138   0.02169   0.01332  -0.0255   0.6201   1.0000
   4.750   0.6136   0.02138   0.01290  -0.0185   0.5128   1.0000
   5.000   0.5983   0.02319   0.01259  -0.0105   0.2087   1.0000
   5.250   0.5903   0.02565   0.01405  -0.0059   0.0777   1.0000
   5.500   0.5924   0.02729   0.01540  -0.0020   0.0413   1.0000
   5.750   0.5985   0.02856   0.01670   0.0014   0.0339   1.0000
   6.000   0.6048   0.02983   0.01816   0.0049   0.0298   1.0000
   6.250   0.6118   0.03108   0.01957   0.0083   0.0274   1.0000
   6.500   0.6201   0.03239   0.02103   0.0113   0.0257   1.0000
   6.750   0.6318   0.03400   0.02277   0.0140   0.0238   1.0000
   7.000   0.6574   0.03618   0.02509   0.0149   0.0226   1.0000
   7.250   0.6903   0.03843   0.02764   0.0150   0.0221   1.0000
   7.500   0.7187   0.04119   0.03077   0.0156   0.0216   1.0000
   7.750   0.7381   0.04391   0.03384   0.0170   0.0214   1.0000
   8.000   0.7516   0.04672   0.03705   0.0191   0.0210   1.0000
   8.250   0.7596   0.04966   0.04039   0.0217   0.0206   1.0000
   8.500   0.7632   0.05256   0.04364   0.0244   0.0202   1.0000
   8.750   0.7634   0.05547   0.04686   0.0272   0.0203   1.0000
   9.000   0.7589   0.05837   0.05007   0.0302   0.0198   1.0000
   9.250   0.7514   0.06136   0.05329   0.0330   0.0201   1.0000
   9.500   0.7390   0.06413   0.05624   0.0362   0.0200   1.0000
   9.750   0.7254   0.06710   0.05938   0.0385   0.0201   1.0000
  10.000   0.7095   0.07046   0.06290   0.0399   0.0200   1.0000
  10.250   0.6952   0.07411   0.06667   0.0402   0.0204   1.0000
  10.500   0.6766   0.07859   0.07127   0.0393   0.0203   1.0000
  10.750   0.6621   0.08323   0.07598   0.0377   0.0208   1.0000
  11.000   0.6482   0.08832   0.08114   0.0353   0.0212   1.0000
  11.250   0.6340   0.09419   0.08704   0.0322   0.0214   1.0000
  11.500   0.6258   0.09952   0.09236   0.0296   0.0220   1.0000
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