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BE50 (original) (be50-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 500,000
Max Cl/Cd: 102.14 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50-il-500000.txt
Download as CSV file: xf-be50-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3878   0.08663   0.08449  -0.0244   1.0000   0.0191
  -8.250  -0.3873   0.08465   0.08253  -0.0230   1.0000   0.0195
  -8.000  -0.3858   0.08250   0.08042  -0.0223   1.0000   0.0198
  -7.750  -0.3858   0.08022   0.07817  -0.0220   1.0000   0.0201
  -7.500  -0.3856   0.07781   0.07577  -0.0221   1.0000   0.0204
  -7.250  -0.3841   0.07519   0.07318  -0.0227   1.0000   0.0209
  -7.000  -0.3805   0.07227   0.07028  -0.0241   1.0000   0.0215
  -6.250  -0.2501   0.04294   0.04051  -0.0707   0.9923   0.0262
  -6.000  -0.2217   0.04198   0.03955  -0.0730   0.9894   0.0277
  -5.750  -0.1823   0.03842   0.03585  -0.0790   0.9869   0.0301
  -5.500  -0.1270   0.03288   0.02973  -0.0874   0.9849   0.0349
  -5.250  -0.0881   0.02483   0.02128  -0.0952   0.9836   0.0378
  -5.000  -0.0536   0.02361   0.01995  -0.0974   0.9803   0.0413
  -4.750  -0.0100   0.01699   0.01234  -0.1010   0.9780   0.0328
  -4.500   0.0288   0.01487   0.00986  -0.1035   0.9756   0.0328
  -4.250   0.0682   0.01351   0.00826  -0.1058   0.9734   0.0335
  -4.000   0.1061   0.01232   0.00687  -0.1078   0.9711   0.0338
  -3.750   0.1396   0.01149   0.00593  -0.1088   0.9663   0.0343
  -3.500   0.1717   0.01080   0.00516  -0.1094   0.9601   0.0346
  -3.250   0.2039   0.00994   0.00421  -0.1101   0.9541   0.0358
  -3.000   0.2321   0.00921   0.00343  -0.1099   0.9444   0.0373
  -2.750   0.2600   0.00876   0.00294  -0.1096   0.9339   0.0391
  -2.500   0.2874   0.00844   0.00259  -0.1091   0.9216   0.0412
  -2.250   0.3144   0.00818   0.00227  -0.1086   0.9068   0.0437
  -2.000   0.3414   0.00798   0.00200  -0.1080   0.8889   0.0467
  -1.750   0.3687   0.00762   0.00171  -0.1075   0.8680   0.0804
  -1.500   0.3957   0.00723   0.00159  -0.1073   0.8417   0.1995
  -1.250   0.4227   0.00695   0.00153  -0.1071   0.8141   0.3099
  -1.000   0.4497   0.00683   0.00155  -0.1068   0.7877   0.4207
  -0.750   0.4767   0.00678   0.00158  -0.1065   0.7628   0.4908
  -0.500   0.5037   0.00667   0.00161  -0.1063   0.7399   0.5823
   0.000   0.5504   0.00598   0.00160  -0.1037   0.6976   1.0000
   0.250   0.5780   0.00613   0.00162  -0.1035   0.6754   1.0000
   0.500   0.6054   0.00630   0.00165  -0.1033   0.6541   1.0000
   0.750   0.6330   0.00646   0.00169  -0.1032   0.6319   1.0000
   1.000   0.6603   0.00663   0.00174  -0.1030   0.6095   1.0000
   1.250   0.6877   0.00681   0.00181  -0.1028   0.5852   1.0000
   1.500   0.7148   0.00701   0.00189  -0.1026   0.5576   1.0000
   1.750   0.7415   0.00726   0.00198  -0.1024   0.5272   1.0000
   2.000   0.7682   0.00753   0.00210  -0.1021   0.4959   1.0000
   2.250   0.7947   0.00783   0.00224  -0.1019   0.4503   1.0000
   2.500   0.8205   0.00824   0.00240  -0.1016   0.4057   1.0000
   3.000   0.8734   0.00888   0.00282  -0.1012   0.3660   1.0000
   3.500   0.9269   0.00940   0.00327  -0.1009   0.3408   1.0000
   3.750   0.9535   0.00967   0.00348  -0.1008   0.3260   1.0000
   4.000   0.9799   0.00995   0.00369  -0.1006   0.3080   1.0000
   4.250   1.0066   0.01019   0.00392  -0.1004   0.2934   1.0000
   4.500   1.0333   0.01041   0.00412  -0.1003   0.2778   1.0000
   4.750   1.0598   0.01065   0.00433  -0.1001   0.2599   1.0000
   5.000   1.0857   0.01097   0.00456  -0.0999   0.2368   1.0000
   5.250   1.1109   0.01139   0.00486  -0.0996   0.2063   1.0000
   5.500   1.1352   0.01192   0.00524  -0.0992   0.1733   1.0000
   5.750   1.1580   0.01271   0.00576  -0.0986   0.1266   1.0000
   6.000   1.1737   0.01460   0.00700  -0.0972   0.0289   1.0000
   6.250   1.1965   0.01539   0.00777  -0.0964   0.0179   1.0000
   6.500   1.2204   0.01600   0.00845  -0.0957   0.0160   1.0000
   6.750   1.2435   0.01666   0.00920  -0.0950   0.0148   1.0000
   7.000   1.2655   0.01749   0.01011  -0.0941   0.0137   1.0000
   7.250   1.2847   0.01865   0.01141  -0.0927   0.0128   1.0000
   7.500   1.3035   0.01978   0.01266  -0.0914   0.0121   1.0000
   7.750   1.3234   0.02069   0.01368  -0.0902   0.0116   1.0000
   8.000   1.3411   0.02182   0.01492  -0.0888   0.0113   1.0000
   8.250   1.3576   0.02304   0.01625  -0.0871   0.0109   1.0000
   8.500   1.3728   0.02435   0.01767  -0.0853   0.0106   1.0000
   8.750   1.3869   0.02576   0.01919  -0.0834   0.0103   1.0000
   9.000   1.3999   0.02726   0.02080  -0.0814   0.0101   1.0000
   9.250   1.4118   0.02890   0.02257  -0.0792   0.0099   1.0000
   9.500   1.4225   0.03069   0.02449  -0.0770   0.0097   1.0000
   9.750   1.4323   0.03266   0.02661  -0.0747   0.0097   1.0000
  10.000   1.4404   0.03489   0.02902  -0.0721   0.0097   1.0000
  10.250   1.4458   0.03742   0.03177  -0.0692   0.0099   1.0000
  10.500   1.4484   0.03993   0.03450  -0.0662   0.0099   1.0000
  10.750   1.4484   0.04240   0.03717  -0.0632   0.0099   1.0000
  11.000   1.4489   0.04451   0.03939  -0.0608   0.0097   1.0000
  11.250   1.4453   0.04712   0.04218  -0.0583   0.0096   1.0000
  11.500   1.4185   0.05366   0.04932  -0.0545   0.0107   1.0000
  11.750   1.3994   0.05891   0.05485  -0.0528   0.0113   1.0000
  12.000   1.3786   0.06454   0.06071  -0.0522   0.0117   1.0000
  12.250   1.2445   0.06070   0.05699  -0.0404   0.0106   1.0000
  12.500   1.2208   0.06714   0.06363  -0.0407   0.0107   1.0000
  12.750   1.1951   0.07406   0.07074  -0.0417   0.0110   1.0000
  13.000   1.1719   0.08054   0.07738  -0.0433   0.0110   1.0000
  13.250   1.1473   0.08733   0.08433  -0.0455   0.0111   1.0000
  13.500   1.1230   0.09409   0.09125  -0.0481   0.0112   1.0000
  13.750   1.0931   0.10147   0.09877  -0.0511   0.0115   1.0000
  14.000   1.0597   0.10772   0.10516  -0.0536   0.0117   1.0000
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