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MUE 139 (mue139-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: MUE 139 (mue139-il)
Reynolds number: 50,000
Max Cl/Cd: 27.3 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mue139-il-50000-n5.txt
Download as CSV file: xf-mue139-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MUE 139                                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2258   0.11209   0.10506  -0.0236   1.0000   0.1409
  -9.000  -0.2365   0.11090   0.10399  -0.0254   1.0000   0.1452
  -8.750  -0.2528   0.10989   0.10313  -0.0275   1.0000   0.1463
  -8.500  -0.2372   0.10556   0.09888  -0.0264   1.0000   0.1480
  -8.250  -0.2198   0.10215   0.09554  -0.0249   1.0000   0.1510
  -8.000  -0.2156   0.09976   0.09326  -0.0244   1.0000   0.1536
  -7.750  -0.2166   0.09761   0.09124  -0.0241   1.0000   0.1557
  -7.500  -0.2217   0.09567   0.08947  -0.0236   1.0000   0.1570
  -7.000  -0.2500   0.08476   0.07866  -0.0359   0.9658   0.1028
  -6.750  -0.2256   0.08014   0.07401  -0.0416   0.9428   0.1018
  -6.500  -0.2005   0.07512   0.06891  -0.0489   0.9224   0.1013
  -6.250  -0.1761   0.07022   0.06389  -0.0554   0.9024   0.1005
  -6.000  -0.1534   0.06534   0.05885  -0.0613   0.8825   0.0991
  -5.750  -0.1338   0.06060   0.05391  -0.0663   0.8623   0.0979
  -5.500  -0.1155   0.05640   0.04945  -0.0698   0.8424   0.0980
  -5.250  -0.0976   0.05268   0.04544  -0.0722   0.8235   0.0995
  -5.000  -0.0801   0.04914   0.04153  -0.0739   0.8057   0.1006
  -4.750  -0.0623   0.04592   0.03790  -0.0747   0.7884   0.1013
  -4.500  -0.0446   0.04299   0.03452  -0.0748   0.7710   0.1021
  -4.250  -0.0263   0.04043   0.03143  -0.0745   0.7542   0.1043
  -4.000  -0.0041   0.03922   0.03016  -0.0738   0.7370   0.1066
  -3.750   0.0174   0.03771   0.02837  -0.0730   0.7205   0.1088
  -3.500   0.0394   0.03608   0.02636  -0.0722   0.7046   0.1108
  -3.250   0.0623   0.03460   0.02442  -0.0713   0.6895   0.1143
  -3.000   0.0859   0.03325   0.02263  -0.0704   0.6747   0.1176
  -2.750   0.1088   0.03231   0.02158  -0.0694   0.6584   0.1202
  -2.500   0.1326   0.03146   0.02054  -0.0685   0.6430   0.1238
  -2.250   0.1577   0.03063   0.01936  -0.0676   0.6286   0.1287
  -2.000   0.1837   0.02977   0.01822  -0.0669   0.6153   0.1326
  -1.750   0.2090   0.02913   0.01750  -0.0661   0.6014   0.1371
  -1.500   0.2347   0.02861   0.01679  -0.0654   0.5877   0.1431
  -1.250   0.2621   0.02804   0.01601  -0.0648   0.5757   0.1484
  -1.000   0.2898   0.02756   0.01545  -0.0643   0.5640   0.1551
  -0.750   0.3177   0.02727   0.01494  -0.0639   0.5515   0.1630
  -0.500   0.3462   0.02686   0.01450  -0.0636   0.5413   0.1710
  -0.250   0.3733   0.02664   0.01417  -0.0631   0.5303   0.1815
   0.000   0.3998   0.02641   0.01393  -0.0626   0.5204   0.1929
   0.250   0.4261   0.02621   0.01373  -0.0619   0.5109   0.2078
   0.500   0.4513   0.02609   0.01368  -0.0613   0.5017   0.2277
   0.750   0.4766   0.02591   0.01366  -0.0606   0.4931   0.2626
   1.000   0.5005   0.02560   0.01367  -0.0598   0.4849   0.3474
   1.500   0.5910   0.02454   0.01380  -0.0654   0.4662   1.0000
   1.750   0.6142   0.02500   0.01405  -0.0644   0.4587   1.0000
   2.000   0.6398   0.02536   0.01410  -0.0636   0.4529   1.0000
   2.250   0.6603   0.02601   0.01470  -0.0624   0.4447   1.0000
   2.500   0.6841   0.02647   0.01496  -0.0615   0.4383   1.0000
   2.750   0.7076   0.02700   0.01532  -0.0606   0.4324   1.0000
   3.000   0.7281   0.02771   0.01600  -0.0595   0.4255   1.0000
   3.250   0.7519   0.02825   0.01639  -0.0586   0.4201   1.0000
   3.500   0.7761   0.02880   0.01678  -0.0578   0.4154   1.0000
   3.750   0.7939   0.02972   0.01775  -0.0566   0.4087   1.0000
   4.000   0.8161   0.03036   0.01831  -0.0556   0.4033   1.0000
   4.250   0.8417   0.03083   0.01861  -0.0550   0.3990   1.0000
   4.500   0.8576   0.03193   0.01980  -0.0536   0.3933   1.0000
   4.750   0.8758   0.03290   0.02080  -0.0524   0.3881   1.0000
   5.000   0.8984   0.03358   0.02139  -0.0515   0.3838   1.0000
   5.250   0.9250   0.03405   0.02171  -0.0510   0.3803   1.0000
   5.500   0.9324   0.03568   0.02356  -0.0490   0.3742   1.0000
   5.750   0.9483   0.03679   0.02471  -0.0477   0.3693   1.0000
   6.000   0.9704   0.03750   0.02536  -0.0469   0.3655   1.0000
   6.250   0.9967   0.03801   0.02575  -0.0464   0.3623   1.0000
   6.500   0.9926   0.04042   0.02845  -0.0437   0.3563   1.0000
   6.750   1.0029   0.04186   0.02995  -0.0420   0.3515   1.0000
   7.000   1.0248   0.04251   0.03057  -0.0412   0.3478   1.0000
   7.250   1.0501   0.04304   0.03102  -0.0406   0.3446   1.0000
   7.500   1.0175   0.04729   0.03561  -0.0365   0.3379   1.0000
   7.750   1.0192   0.04921   0.03758  -0.0345   0.3331   1.0000
   8.000   1.0487   0.04924   0.03754  -0.0340   0.3297   1.0000
   8.250   0.9120   0.06303   0.05172  -0.0307   0.3181   1.0000
   8.500   0.9292   0.06392   0.05259  -0.0298   0.3144   1.0000
   8.750   0.9662   0.06256   0.05116  -0.0282   0.3122   1.0000
   9.250   0.8996   0.07735   0.06611  -0.0316   0.2953   1.0000
  10.000   0.8891   0.08899   0.07782  -0.0334   0.2775   1.0000
  10.500   0.8620   0.09985   0.08877  -0.0364   0.2631   1.0000
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