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BOEING 103 AIRFOIL (boe103-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: BOEING 103 AIRFOIL (boe103-il)
Reynolds number: 50,000
Max Cl/Cd: 35.02 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-boe103-il-50000-n5.txt
Download as CSV file: xf-boe103-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 103 AIRFOIL                              
  
 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  -0.3763   0.11732   0.10982  -0.0423   1.0000   0.0765
 -10.500  -0.3720   0.11375   0.10629  -0.0424   1.0000   0.0762
 -10.250  -0.3700   0.11021   0.10280  -0.0428   1.0000   0.0758
 -10.000  -0.3689   0.10672   0.09937  -0.0430   1.0000   0.0753
  -9.750  -0.3689   0.10328   0.09599  -0.0432   1.0000   0.0744
  -9.500  -0.3712   0.09979   0.09257  -0.0434   1.0000   0.0733
  -9.250  -0.3767   0.09620   0.08907  -0.0438   1.0000   0.0723
  -9.000  -0.3857   0.09253   0.08551  -0.0441   1.0000   0.0713
  -8.750  -0.3993   0.08883   0.08193  -0.0444   1.0000   0.0703
  -8.500  -0.4200   0.08513   0.07837  -0.0443   1.0000   0.0694
  -8.250  -0.4463   0.08061   0.07398  -0.0450   1.0000   0.0682
  -7.750  -0.5129   0.06804   0.06112  -0.0467   1.0000   0.0653
  -7.500  -0.5103   0.06631   0.05949  -0.0446   1.0000   0.0663
  -7.250  -0.5122   0.06379   0.05691  -0.0431   1.0000   0.0671
  -7.000  -0.5138   0.06085   0.05385  -0.0419   1.0000   0.0679
  -6.750  -0.5136   0.05759   0.05040  -0.0409   1.0000   0.0685
  -6.500  -0.5107   0.05412   0.04665  -0.0402   1.0000   0.0689
  -6.250  -0.4860   0.04944   0.04145  -0.0436   0.9941   0.0692
  -6.000  -0.4584   0.04555   0.03703  -0.0464   0.9874   0.0700
  -5.750  -0.4285   0.04254   0.03351  -0.0488   0.9810   0.0723
  -5.500  -0.3965   0.03965   0.03000  -0.0510   0.9748   0.0749
  -5.250  -0.3652   0.03719   0.02695  -0.0525   0.9682   0.0763
  -5.000  -0.3307   0.03530   0.02480  -0.0545   0.9625   0.0779
  -4.750  -0.2997   0.03393   0.02327  -0.0556   0.9552   0.0801
  -4.500  -0.2642   0.03278   0.02190  -0.0574   0.9491   0.0843
  -4.250  -0.2328   0.03166   0.02047  -0.0581   0.9416   0.0888
  -4.000  -0.1977   0.03064   0.01942  -0.0597   0.9354   0.0928
  -3.750  -0.1663   0.02982   0.01851  -0.0604   0.9280   0.0980
  -3.500  -0.1321   0.02903   0.01759  -0.0615   0.9211   0.1057
  -3.250  -0.0977   0.02837   0.01691  -0.0629   0.9143   0.1200
  -3.000  -0.0668   0.02769   0.01629  -0.0638   0.9063   0.1429
  -2.750  -0.0278   0.02684   0.01556  -0.0661   0.9012   0.1878
  -2.500  -0.0032   0.02624   0.01522  -0.0661   0.8914   0.2434
  -2.250   0.0301   0.02499   0.01505  -0.0678   0.8860   0.4112
  -2.000   0.0466   0.02422   0.01527  -0.0648   0.8766   0.6250
  -1.750   0.0786   0.02385   0.01534  -0.0633   0.8711   0.8063
  -1.500   0.1511   0.02378   0.01510  -0.0704   0.8686   0.9560
  -1.250   0.1933   0.02391   0.01494  -0.0738   0.8587   1.0000
  -1.000   0.2304   0.02386   0.01461  -0.0756   0.8522   1.0000
  -0.750   0.2495   0.02408   0.01461  -0.0744   0.8401   1.0000
  -0.500   0.2776   0.02419   0.01452  -0.0746   0.8309   1.0000
  -0.250   0.3079   0.02425   0.01438  -0.0750   0.8218   1.0000
   0.000   0.3320   0.02440   0.01437  -0.0744   0.8101   1.0000
   0.250   0.3680   0.02425   0.01406  -0.0754   0.8014   1.0000
   0.500   0.3940   0.02429   0.01397  -0.0748   0.7890   1.0000
   0.750   0.4186   0.02438   0.01394  -0.0740   0.7764   1.0000
   1.000   0.4481   0.02436   0.01380  -0.0739   0.7658   1.0000
   1.250   0.4785   0.02432   0.01366  -0.0740   0.7557   1.0000
   1.500   0.5012   0.02452   0.01378  -0.0729   0.7433   1.0000
   1.750   0.5283   0.02459   0.01378  -0.0725   0.7323   1.0000
   2.000   0.5599   0.02451   0.01363  -0.0726   0.7226   1.0000
   2.250   0.5823   0.02473   0.01381  -0.0715   0.7096   1.0000
   2.500   0.6073   0.02487   0.01391  -0.0707   0.6974   1.0000
   2.750   0.6370   0.02484   0.01383  -0.0705   0.6865   1.0000
   3.000   0.6646   0.02488   0.01384  -0.0700   0.6744   1.0000
   3.250   0.6880   0.02507   0.01403  -0.0689   0.6606   1.0000
   3.500   0.7127   0.02523   0.01418  -0.0680   0.6470   1.0000
   3.750   0.7385   0.02536   0.01429  -0.0673   0.6335   1.0000
   4.000   0.7651   0.02545   0.01437  -0.0666   0.6198   1.0000
   4.250   0.7920   0.02554   0.01445  -0.0660   0.6057   1.0000
   4.500   0.8181   0.02566   0.01455  -0.0652   0.5909   1.0000
   4.750   0.8422   0.02586   0.01475  -0.0642   0.5751   1.0000
   5.000   0.8654   0.02610   0.01500  -0.0631   0.5587   1.0000
   5.250   0.8870   0.02640   0.01529  -0.0618   0.5414   1.0000
   5.500   0.9074   0.02673   0.01563  -0.0603   0.5231   1.0000
   5.750   0.9265   0.02705   0.01596  -0.0586   0.5031   1.0000
   6.000   0.9457   0.02729   0.01615  -0.0568   0.4817   1.0000
   6.250   0.9640   0.02756   0.01633  -0.0549   0.4598   1.0000
   6.500   0.9794   0.02801   0.01675  -0.0528   0.4371   1.0000
   6.750   0.9964   0.02845   0.01711  -0.0509   0.4161   1.0000
   7.000   1.0130   0.02899   0.01758  -0.0491   0.3968   1.0000
   7.250   1.0287   0.02964   0.01821  -0.0473   0.3786   1.0000
   7.500   1.0442   0.03035   0.01890  -0.0455   0.3612   1.0000
   7.750   1.0587   0.03112   0.01967  -0.0436   0.3439   1.0000
   8.000   1.0714   0.03195   0.02048  -0.0416   0.3269   1.0000
   8.250   1.0829   0.03286   0.02137  -0.0394   0.3103   1.0000
   8.500   1.0939   0.03386   0.02236  -0.0374   0.2941   1.0000
   8.750   1.1048   0.03493   0.02347  -0.0354   0.2788   1.0000
   9.000   1.1156   0.03607   0.02462  -0.0335   0.2644   1.0000
   9.250   1.1264   0.03727   0.02580  -0.0317   0.2511   1.0000
   9.500   1.1371   0.03851   0.02703  -0.0300   0.2388   1.0000
   9.750   1.1473   0.03988   0.02848  -0.0284   0.2269   1.0000
  10.000   1.1581   0.04127   0.02993  -0.0269   0.2167   1.0000
  10.250   1.1701   0.04254   0.03114  -0.0255   0.2083   1.0000
  10.500   1.1807   0.04412   0.03287  -0.0242   0.1997   1.0000
  10.750   1.1959   0.04534   0.03404  -0.0231   0.1935   1.0000
  11.000   1.2080   0.04705   0.03595  -0.0221   0.1874   1.0000
  11.250   1.2224   0.04853   0.03755  -0.0211   0.1822   1.0000
  11.500   1.2404   0.04981   0.03881  -0.0203   0.1777   1.0000
  11.750   1.2463   0.05199   0.04127  -0.0191   0.1731   1.0000
  12.000   1.2547   0.05391   0.04335  -0.0181   0.1688   1.0000
  12.250   1.2710   0.05528   0.04474  -0.0173   0.1649   1.0000
  12.500   1.2776   0.05757   0.04722  -0.0163   0.1617   1.0000
  12.750   1.2742   0.06062   0.05058  -0.0152   0.1588   1.0000
  13.000   1.2714   0.06362   0.05381  -0.0144   0.1557   1.0000
  13.250   1.2742   0.06608   0.05640  -0.0136   0.1526   1.0000
  13.500   1.2951   0.06703   0.05727  -0.0130   0.1490   1.0000
  13.750   1.2691   0.07230   0.06293  -0.0127   0.1471   1.0000
  14.000   1.2382   0.07872   0.06967  -0.0134   0.1454   1.0000
  14.250   1.1944   0.08759   0.07884  -0.0159   0.1440   1.0000
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