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BE50 (original) (be50-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 100,000
Max Cl/Cd: 59.65 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-be50-il-100000-n5.txt
Download as CSV file: xf-be50-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3641   0.09306   0.08829  -0.0226   1.0000   0.0506
  -8.000  -0.3703   0.09112   0.08647  -0.0264   1.0000   0.0534
  -7.750  -0.3677   0.08805   0.08348  -0.0312   1.0000   0.0540
  -7.500  -0.3613   0.08438   0.07984  -0.0349   1.0000   0.0541
  -7.250  -0.3583   0.07890   0.07436  -0.0305   1.0000   0.0396
  -7.000  -0.3514   0.07503   0.07053  -0.0336   1.0000   0.0397
  -6.750  -0.3409   0.07068   0.06618  -0.0378   1.0000   0.0400
  -6.500  -0.3298   0.06646   0.06197  -0.0407   1.0000   0.0397
  -6.250  -0.3171   0.06228   0.05776  -0.0433   1.0000   0.0388
  -6.000  -0.2987   0.05727   0.05268  -0.0480   1.0000   0.0380
  -5.750  -0.2737   0.05138   0.04662  -0.0542   1.0000   0.0376
  -5.500  -0.2369   0.04355   0.03838  -0.0634   1.0000   0.0395
  -5.250  -0.2021   0.03722   0.03151  -0.0695   1.0000   0.0401
  -5.000  -0.1684   0.03232   0.02599  -0.0736   1.0000   0.0403
  -4.750  -0.1271   0.02829   0.02133  -0.0786   0.9973   0.0428
  -4.500  -0.0871   0.02581   0.01842  -0.0821   0.9939   0.0444
  -4.250  -0.0474   0.02350   0.01560  -0.0851   0.9901   0.0451
  -4.000  -0.0076   0.02175   0.01341  -0.0878   0.9866   0.0463
  -3.750   0.0302   0.02038   0.01173  -0.0899   0.9817   0.0477
  -3.500   0.0692   0.01944   0.01054  -0.0923   0.9771   0.0517
  -3.250   0.1065   0.01855   0.00941  -0.0941   0.9707   0.0539
  -3.000   0.1469   0.01756   0.00837  -0.0967   0.9653   0.0558
  -2.750   0.1844   0.01685   0.00765  -0.0987   0.9567   0.0590
  -2.500   0.2259   0.01623   0.00693  -0.1013   0.9496   0.0646
  -2.250   0.2626   0.01564   0.00634  -0.1029   0.9392   0.0752
  -2.000   0.2975   0.01499   0.00593  -0.1043   0.9277   0.1259
  -1.750   0.3311   0.01440   0.00562  -0.1054   0.9157   0.2233
  -1.500   0.3637   0.01371   0.00559  -0.1064   0.9032   0.4224
  -1.250   0.3933   0.01304   0.00546  -0.1064   0.8890   0.5919
  -1.000   0.4162   0.01203   0.00511  -0.1041   0.8718   1.0000
  -0.750   0.4485   0.01197   0.00484  -0.1045   0.8547   1.0000
  -0.500   0.4795   0.01195   0.00463  -0.1047   0.8368   1.0000
  -0.250   0.5098   0.01195   0.00447  -0.1047   0.8188   1.0000
   0.000   0.5399   0.01198   0.00432  -0.1047   0.8002   1.0000
   0.250   0.5694   0.01203   0.00422  -0.1046   0.7808   1.0000
   0.500   0.5978   0.01212   0.00418  -0.1043   0.7602   1.0000
   0.750   0.6262   0.01224   0.00414  -0.1040   0.7393   1.0000
   1.000   0.6537   0.01239   0.00418  -0.1036   0.7173   1.0000
   1.250   0.6809   0.01258   0.00423  -0.1031   0.6952   1.0000
   1.500   0.7076   0.01278   0.00433  -0.1026   0.6712   1.0000
   1.750   0.7341   0.01300   0.00445  -0.1020   0.6464   1.0000
   2.000   0.7602   0.01325   0.00460  -0.1014   0.6200   1.0000
   2.250   0.7861   0.01352   0.00476  -0.1008   0.5914   1.0000
   2.500   0.8116   0.01381   0.00494  -0.1002   0.5608   1.0000
   2.750   0.8369   0.01415   0.00514  -0.0995   0.5300   1.0000
   3.000   0.8620   0.01451   0.00542  -0.0989   0.5002   1.0000
   3.250   0.8872   0.01489   0.00572  -0.0983   0.4691   1.0000
   3.500   0.9121   0.01529   0.00603  -0.0978   0.4399   1.0000
   3.750   0.9368   0.01574   0.00637  -0.0972   0.4163   1.0000
   4.000   0.9615   0.01623   0.00681  -0.0966   0.3969   1.0000
   4.250   0.9862   0.01673   0.00727  -0.0961   0.3803   1.0000
   4.500   1.0109   0.01725   0.00778  -0.0956   0.3656   1.0000
   4.750   1.0358   0.01777   0.00833  -0.0951   0.3520   1.0000
   5.000   1.0606   0.01829   0.00894  -0.0946   0.3390   1.0000
   5.250   1.0853   0.01883   0.00956  -0.0941   0.3265   1.0000
   5.500   1.1093   0.01937   0.01017  -0.0935   0.3109   1.0000
   5.750   1.1322   0.01989   0.01072  -0.0928   0.2905   1.0000
   6.000   1.1555   0.02031   0.01131  -0.0922   0.2667   1.0000
   6.250   1.1778   0.02078   0.01181  -0.0914   0.2368   1.0000
   6.500   1.1977   0.02152   0.01236  -0.0905   0.1904   1.0000
   6.750   1.2154   0.02276   0.01326  -0.0894   0.1253   1.0000
   7.000   1.2255   0.02530   0.01507  -0.0875   0.0426   1.0000
   7.250   1.2408   0.02704   0.01683  -0.0858   0.0290   1.0000
   7.500   1.2553   0.02876   0.01870  -0.0840   0.0246   1.0000
   7.750   1.2702   0.03025   0.02049  -0.0823   0.0227   1.0000
   8.000   1.2837   0.03177   0.02226  -0.0804   0.0211   1.0000
   8.250   1.2956   0.03333   0.02401  -0.0785   0.0193   1.0000
   8.500   1.3048   0.03503   0.02587  -0.0764   0.0179   1.0000
   8.750   1.3077   0.03720   0.02819  -0.0737   0.0169   1.0000
   9.000   1.3119   0.03908   0.03024  -0.0709   0.0165   1.0000
   9.250   1.3143   0.04106   0.03240  -0.0680   0.0161   1.0000
   9.500   1.3168   0.04322   0.03473  -0.0654   0.0158   1.0000
   9.750   1.3197   0.04554   0.03722  -0.0631   0.0156   1.0000
  10.000   1.3229   0.04803   0.03990  -0.0610   0.0153   1.0000
  10.250   1.3259   0.05069   0.04276  -0.0592   0.0151   1.0000
  10.500   1.3279   0.05357   0.04592  -0.0575   0.0149   1.0000
  10.750   1.3281   0.05667   0.04924  -0.0560   0.0147   1.0000
  11.000   1.3260   0.05999   0.05281  -0.0549   0.0144   1.0000
  11.250   1.3216   0.06358   0.05664  -0.0542   0.0141   1.0000
  11.500   1.3152   0.06748   0.06077  -0.0540   0.0138   1.0000
  11.750   1.3068   0.07181   0.06534  -0.0544   0.0136   1.0000
  12.000   1.2966   0.07654   0.07030  -0.0554   0.0135   1.0000
  12.250   1.2850   0.08174   0.07573  -0.0570   0.0133   1.0000
  12.500   1.2718   0.08748   0.08169  -0.0592   0.0132   1.0000
  12.750   1.2572   0.09378   0.08821  -0.0621   0.0132   1.0000
  13.000   1.2412   0.10072   0.09538  -0.0657   0.0133   1.0000
  13.250   1.2239   0.10837   0.10325  -0.0701   0.0134   1.0000
  13.500   1.2041   0.11731   0.11242  -0.0755   0.0136   1.0000
  13.750   1.1830   0.12731   0.12262  -0.0819   0.0139   1.0000
  14.000   1.1611   0.13827   0.13376  -0.0890   0.0144   1.0000
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