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BE50 (original) (be50-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 200,000
Max Cl/Cd: 73.94 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-be50-il-200000-n5.txt
Download as CSV file: xf-be50-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BE50 (original)                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3764   0.08599   0.08262  -0.0236   1.0000   0.0171
  -8.000  -0.3788   0.08295   0.07964  -0.0241   1.0000   0.0171
  -7.750  -0.3792   0.07933   0.07608  -0.0261   1.0000   0.0176
  -7.500  -0.3771   0.07505   0.07184  -0.0295   1.0000   0.0182
  -7.250  -0.3715   0.06997   0.06680  -0.0342   1.0000   0.0189
  -7.000  -0.3655   0.06529   0.06213  -0.0376   1.0000   0.0192
  -6.750  -0.3423   0.05918   0.05597  -0.0454   0.9980   0.0195
  -6.500  -0.3057   0.05366   0.05034  -0.0546   0.9943   0.0202
  -6.250  -0.2667   0.04797   0.04451  -0.0638   0.9902   0.0214
  -6.000  -0.2207   0.04045   0.03667  -0.0749   0.9871   0.0239
  -5.750  -0.1715   0.02984   0.02527  -0.0862   0.9844   0.0252
  -5.500  -0.1324   0.02610   0.02086  -0.0903   0.9810   0.0274
  -5.250  -0.0936   0.02189   0.01593  -0.0944   0.9785   0.0288
  -5.000  -0.0560   0.01943   0.01304  -0.0973   0.9763   0.0300
  -4.750  -0.0222   0.01831   0.01174  -0.0990   0.9716   0.0321
  -4.500   0.0152   0.01696   0.01010  -0.1011   0.9676   0.0331
  -4.250   0.0542   0.01573   0.00860  -0.1034   0.9643   0.0340
  -4.000   0.0866   0.01482   0.00753  -0.1042   0.9567   0.0350
  -3.750   0.1231   0.01399   0.00657  -0.1059   0.9515   0.0361
  -3.500   0.1538   0.01336   0.00584  -0.1063   0.9424   0.0372
  -3.250   0.1869   0.01287   0.00527  -0.1072   0.9343   0.0394
  -3.000   0.2183   0.01243   0.00476  -0.1077   0.9241   0.0408
  -2.750   0.2485   0.01195   0.00423  -0.1080   0.9118   0.0419
  -2.500   0.2788   0.01152   0.00374  -0.1083   0.8983   0.0448
  -2.250   0.3091   0.01120   0.00338  -0.1085   0.8833   0.0496
  -2.000   0.3393   0.01087   0.00305  -0.1087   0.8671   0.0631
  -1.750   0.3686   0.01049   0.00283  -0.1088   0.8477   0.1205
  -1.500   0.3975   0.01020   0.00266  -0.1087   0.8256   0.1876
  -1.250   0.4254   0.00975   0.00260  -0.1088   0.8016   0.3234
  -1.000   0.4524   0.00954   0.00258  -0.1084   0.7775   0.4405
  -0.750   0.4786   0.00933   0.00257  -0.1078   0.7548   0.5467
  -0.500   0.5024   0.00893   0.00256  -0.1067   0.7345   0.6906
  -0.250   0.5245   0.00851   0.00242  -0.1047   0.7145   1.0000
   0.250   0.5791   0.00885   0.00241  -0.1041   0.6747   1.0000
   0.500   0.6062   0.00903   0.00245  -0.1038   0.6542   1.0000
   0.750   0.6332   0.00922   0.00249  -0.1035   0.6327   1.0000
   1.000   0.6600   0.00942   0.00255  -0.1031   0.6095   1.0000
   1.250   0.6867   0.00963   0.00264  -0.1028   0.5836   1.0000
   1.500   0.7131   0.00987   0.00273  -0.1024   0.5552   1.0000
   1.750   0.7392   0.01015   0.00284  -0.1020   0.5265   1.0000
   2.000   0.7653   0.01043   0.00300  -0.1017   0.4983   1.0000
   2.250   0.7914   0.01072   0.00316  -0.1013   0.4642   1.0000
   2.500   0.8169   0.01108   0.00334  -0.1009   0.4256   1.0000
   2.750   0.8423   0.01146   0.00355  -0.1005   0.3985   1.0000
   3.000   0.8680   0.01183   0.00383  -0.1002   0.3793   1.0000
   3.250   0.8938   0.01219   0.00412  -0.0999   0.3638   1.0000
   3.500   0.9198   0.01252   0.00442  -0.0996   0.3507   1.0000
   3.750   0.9459   0.01284   0.00475  -0.0993   0.3395   1.0000
   4.000   0.9718   0.01318   0.00509  -0.0990   0.3286   1.0000
   4.250   0.9975   0.01354   0.00544  -0.0987   0.3184   1.0000
   4.500   1.0233   0.01387   0.00580  -0.0984   0.3057   1.0000
   4.750   1.0487   0.01421   0.00617  -0.0981   0.2876   1.0000
   5.000   1.0743   0.01453   0.00652  -0.0978   0.2711   1.0000
   5.250   1.0991   0.01491   0.00685  -0.0974   0.2462   1.0000
   5.500   1.1228   0.01542   0.00722  -0.0969   0.2098   1.0000
   5.750   1.1455   0.01611   0.00772  -0.0964   0.1713   1.0000
   6.000   1.1660   0.01711   0.00845  -0.0956   0.1175   1.0000
   6.250   1.1804   0.01907   0.00979  -0.0941   0.0336   1.0000
   6.500   1.2013   0.02006   0.01078  -0.0931   0.0195   1.0000
   6.750   1.2224   0.02097   0.01176  -0.0921   0.0158   1.0000
   7.000   1.2430   0.02190   0.01280  -0.0911   0.0137   1.0000
   7.250   1.2619   0.02302   0.01406  -0.0898   0.0122   1.0000
   7.500   1.2796   0.02421   0.01548  -0.0884   0.0116   1.0000
   7.750   1.2968   0.02537   0.01682  -0.0869   0.0112   1.0000
   8.000   1.3120   0.02666   0.01829  -0.0852   0.0108   1.0000
   8.250   1.3252   0.02808   0.01987  -0.0833   0.0104   1.0000
   8.500   1.3370   0.02957   0.02150  -0.0812   0.0100   1.0000
   8.750   1.3479   0.03107   0.02313  -0.0791   0.0094   1.0000
   9.000   1.3570   0.03263   0.02480  -0.0769   0.0089   1.0000
   9.250   1.3620   0.03433   0.02660  -0.0742   0.0084   1.0000
   9.500   1.3641   0.03631   0.02869  -0.0712   0.0082   1.0000
   9.750   1.3657   0.03857   0.03111  -0.0684   0.0080   1.0000
  10.000   1.3665   0.04125   0.03393  -0.0658   0.0078   1.0000
  10.250   1.3689   0.04385   0.03668  -0.0635   0.0077   1.0000
  10.500   1.3713   0.04617   0.03922  -0.0616   0.0076   1.0000
  10.750   1.3720   0.04874   0.04201  -0.0598   0.0075   1.0000
  11.000   1.3709   0.05160   0.04509  -0.0583   0.0074   1.0000
  11.250   1.3677   0.05477   0.04850  -0.0571   0.0074   1.0000
  11.500   1.3626   0.05831   0.05227  -0.0563   0.0073   1.0000
  11.750   1.3555   0.06223   0.05644  -0.0561   0.0073   1.0000
  12.000   1.3467   0.06659   0.06103  -0.0564   0.0072   1.0000
  12.250   1.3361   0.07139   0.06607  -0.0573   0.0072   1.0000
  12.500   1.3243   0.07664   0.07154  -0.0589   0.0072   1.0000
  12.750   1.3111   0.08237   0.07749  -0.0610   0.0072   1.0000
  13.000   1.2970   0.08850   0.08383  -0.0636   0.0072   1.0000
  13.250   1.2822   0.09510   0.09063  -0.0668   0.0072   1.0000
  13.500   1.2670   0.10213   0.09784  -0.0705   0.0073   1.0000
  13.750   1.2515   0.10966   0.10556  -0.0748   0.0073   1.0000
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