Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

BE50 (original) (be50-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 200,000
Max Cl/Cd: 79.79 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50-il-200000.txt
Download as CSV file: xf-be50-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3675   0.08762   0.08425  -0.0216   1.0000   0.0409
  -7.750  -0.3681   0.08507   0.08176  -0.0221   1.0000   0.0424
  -7.500  -0.3670   0.08229   0.07904  -0.0247   1.0000   0.0444
  -7.250  -0.3572   0.07887   0.07564  -0.0357   1.0000   0.0462
  -7.000  -0.3467   0.07357   0.07034  -0.0422   1.0000   0.0467
  -6.750  -0.3522   0.07075   0.06759  -0.0350   1.0000   0.0482
  -6.500  -0.3463   0.06865   0.06552  -0.0328   1.0000   0.0497
  -6.250  -0.3366   0.06589   0.06276  -0.0337   1.0000   0.0516
  -6.000  -0.3217   0.06231   0.05917  -0.0372   1.0000   0.0548
  -5.750  -0.2792   0.05298   0.04953  -0.0543   1.0000   0.0603
  -5.500  -0.2723   0.05132   0.04797  -0.0514   1.0000   0.0617
  -5.250  -0.2589   0.04941   0.04606  -0.0508   1.0000   0.0645
  -5.000  -0.2184   0.04291   0.03915  -0.0606   1.0000   0.0746
  -4.750  -0.2019   0.04130   0.03761  -0.0599   0.9995   0.0774
  -4.500  -0.1489   0.03611   0.03199  -0.0690   0.9964   0.0894
  -4.250  -0.1004   0.03270   0.02820  -0.0754   0.9931   0.1027
  -4.000  -0.0575   0.03027   0.02562  -0.0799   0.9883   0.1172
  -3.750   0.0052   0.02020   0.01382  -0.0855   0.9894   0.0567
  -3.500   0.0508   0.01808   0.01127  -0.0889   0.9860   0.0559
  -3.250   0.0963   0.01696   0.00985  -0.0923   0.9825   0.0580
  -3.000   0.1369   0.01575   0.00845  -0.0946   0.9763   0.0584
  -2.750   0.1808   0.01458   0.00718  -0.0977   0.9721   0.0599
  -2.500   0.2238   0.01358   0.00623  -0.1007   0.9672   0.0641
  -2.250   0.2652   0.01303   0.00568  -0.1033   0.9600   0.0719
  -2.000   0.3120   0.01219   0.00493  -0.1070   0.9560   0.0913
  -1.750   0.3497   0.01099   0.00459  -0.1093   0.9467   0.3035
  -1.500   0.3866   0.01035   0.00450  -0.1110   0.9380   0.4941
  -1.250   0.4175   0.00951   0.00429  -0.1111   0.9273   0.6736
  -1.000   0.4423   0.00875   0.00395  -0.1091   0.9127   1.0000
  -0.750   0.4709   0.00866   0.00372  -0.1088   0.8962   1.0000
  -0.500   0.4993   0.00859   0.00352  -0.1083   0.8784   1.0000
  -0.250   0.5276   0.00852   0.00333  -0.1079   0.8601   1.0000
   0.000   0.5555   0.00849   0.00317  -0.1073   0.8405   1.0000
   0.250   0.5826   0.00853   0.00307  -0.1066   0.8187   1.0000
   0.500   0.6095   0.00861   0.00300  -0.1059   0.7967   1.0000
   0.750   0.6362   0.00873   0.00298  -0.1053   0.7736   1.0000
   1.000   0.6627   0.00889   0.00300  -0.1046   0.7498   1.0000
   1.250   0.6890   0.00909   0.00305  -0.1039   0.7260   1.0000
   1.500   0.7152   0.00929   0.00313  -0.1033   0.7009   1.0000
   1.750   0.7414   0.00950   0.00322  -0.1027   0.6751   1.0000
   2.000   0.7674   0.00973   0.00333  -0.1021   0.6479   1.0000
   2.250   0.7932   0.00998   0.00347  -0.1015   0.6181   1.0000
   2.500   0.8186   0.01026   0.00361  -0.1008   0.5845   1.0000
   2.750   0.8437   0.01058   0.00377  -0.1002   0.5466   1.0000
   3.000   0.8684   0.01100   0.00398  -0.0995   0.5096   1.0000
   3.250   0.8937   0.01138   0.00426  -0.0990   0.4739   1.0000
   3.500   0.9189   0.01177   0.00451  -0.0985   0.4432   1.0000
   3.750   0.9440   0.01221   0.00481  -0.0980   0.4195   1.0000
   4.000   0.9692   0.01268   0.00518  -0.0976   0.4005   1.0000
   4.250   0.9944   0.01318   0.00562  -0.0972   0.3839   1.0000
   4.500   1.0197   0.01368   0.00607  -0.0968   0.3689   1.0000
   4.750   1.0448   0.01419   0.00653  -0.0964   0.3530   1.0000
   5.000   1.0696   0.01458   0.00694  -0.0959   0.3332   1.0000
   5.250   1.0941   0.01495   0.00734  -0.0954   0.3133   1.0000
   5.500   1.1184   0.01534   0.00771  -0.0949   0.2951   1.0000
   5.750   1.1432   0.01556   0.00801  -0.0945   0.2714   1.0000
   6.000   1.1677   0.01585   0.00832  -0.0940   0.2456   1.0000
   6.250   1.1911   0.01630   0.00871  -0.0935   0.2116   1.0000
   6.500   1.2117   0.01721   0.00934  -0.0926   0.1521   1.0000
   6.750   1.2198   0.02016   0.01140  -0.0901   0.0400   1.0000
   7.000   1.2370   0.02169   0.01301  -0.0884   0.0323   1.0000
   7.250   1.2563   0.02275   0.01422  -0.0871   0.0285   1.0000
   7.500   1.2726   0.02412   0.01570  -0.0854   0.0263   1.0000
   7.750   1.2837   0.02604   0.01771  -0.0831   0.0248   1.0000
   8.000   1.2947   0.02809   0.01988  -0.0807   0.0240   1.0000
   8.250   1.3101   0.02968   0.02159  -0.0789   0.0235   1.0000
   8.500   1.3256   0.03150   0.02353  -0.0770   0.0230   1.0000
   8.750   1.3417   0.03337   0.02553  -0.0754   0.0224   1.0000
   9.000   1.3574   0.03511   0.02744  -0.0737   0.0214   1.0000
   9.250   1.3720   0.03696   0.02944  -0.0721   0.0204   1.0000
   9.500   1.3860   0.03938   0.03207  -0.0704   0.0201   1.0000
   9.750   1.3980   0.04214   0.03513  -0.0684   0.0201   1.0000
  10.000   1.4062   0.04527   0.03859  -0.0662   0.0203   1.0000
  10.250   1.4086   0.04871   0.04240  -0.0634   0.0206   1.0000
  10.500   1.4031   0.05215   0.04618  -0.0599   0.0210   1.0000
  10.750   1.3931   0.05571   0.05007  -0.0565   0.0214   1.0000
  11.000   1.3797   0.05953   0.05418  -0.0536   0.0218   1.0000
  11.250   1.3641   0.06366   0.05858  -0.0514   0.0222   1.0000
  11.500   1.3470   0.06819   0.06336  -0.0503   0.0225   1.0000
  11.750   1.3283   0.07323   0.06864  -0.0501   0.0228   1.0000
  12.000   1.3085   0.07884   0.07446  -0.0511   0.0231   1.0000
  12.250   1.2879   0.08502   0.08083  -0.0530   0.0234   1.0000
  12.500   1.2664   0.09192   0.08791  -0.0558   0.0236   1.0000
  12.750   1.2706   0.09536   0.09151  -0.0564   0.0253   1.0000
  13.000   1.2455   0.10336   0.09974  -0.0617   0.0256   1.0000
  13.250   1.2207   0.11224   0.10880  -0.0679   0.0257   1.0000
  13.500   1.1961   0.12219   0.11891  -0.0751   0.0258   1.0000
  13.750   1.1700   0.13380   0.13067  -0.0836   0.0258   1.0000
<< Back to BE50 (original) (be50-il)

Polar data table (+)

Polar graphs


<< Back to BE50 (original) (be50-il)