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MUE 139 (mue139-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: MUE 139 (mue139-il)
Reynolds number: 200,000
Max Cl/Cd: 58.32 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mue139-il-200000.txt
Download as CSV file: xf-mue139-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2237   0.09402   0.09064  -0.0267   1.0000   0.0781
  -8.250  -0.2246   0.09147   0.08817  -0.0274   1.0000   0.0800
  -8.000  -0.2753   0.08923   0.08612  -0.0326   1.0000   0.0822
  -7.750  -0.2571   0.08351   0.08043  -0.0383   0.9790   0.0829
  -7.500  -0.2189   0.08025   0.07716  -0.0386   0.9626   0.0837
  -7.250  -0.1766   0.07654   0.07340  -0.0437   0.9406   0.0855
  -7.000  -0.1347   0.07136   0.06812  -0.0554   0.9089   0.0894
  -6.750  -0.1225   0.06263   0.05911  -0.0740   0.8659   0.0935
  -6.500  -0.0986   0.06058   0.05695  -0.0738   0.8354   0.0944
  -6.250  -0.0833   0.05864   0.05487  -0.0735   0.8089   0.0958
  -6.000  -0.0976   0.05364   0.04918  -0.0813   0.7892   0.1038
  -5.750  -0.0841   0.04963   0.04517  -0.0806   0.7707   0.1047
  -5.500  -0.0668   0.04780   0.04332  -0.0792   0.7519   0.1055
  -5.250  -0.0498   0.04646   0.04193  -0.0777   0.7334   0.1068
  -5.000  -0.0334   0.04496   0.04033  -0.0767   0.7159   0.1090
  -4.750  -0.0255   0.04081   0.03562  -0.0784   0.7023   0.1180
  -4.500  -0.0294   0.02759   0.02084  -0.0769   0.6965   0.0828
  -4.250  -0.0037   0.02789   0.02146  -0.0764   0.6780   0.0856
  -4.000   0.0165   0.02614   0.01939  -0.0752   0.6617   0.0864
  -3.750   0.0375   0.02442   0.01731  -0.0738   0.6455   0.0871
  -3.500   0.0596   0.02294   0.01548  -0.0726   0.6295   0.0880
  -3.250   0.0828   0.02177   0.01395  -0.0713   0.6139   0.0896
  -3.000   0.1069   0.02104   0.01280  -0.0701   0.5983   0.0920
  -2.750   0.1307   0.01995   0.01156  -0.0692   0.5824   0.0944
  -2.500   0.1559   0.01944   0.01098  -0.0684   0.5669   0.0967
  -2.250   0.1814   0.01894   0.01031  -0.0676   0.5528   0.0995
  -2.000   0.2071   0.01863   0.00973  -0.0666   0.5404   0.1030
  -1.750   0.2326   0.01793   0.00891  -0.0659   0.5284   0.1061
  -1.500   0.2586   0.01759   0.00853  -0.0653   0.5169   0.1095
  -1.250   0.2848   0.01739   0.00816  -0.0645   0.5070   0.1137
  -1.000   0.3111   0.01707   0.00773  -0.0638   0.4962   0.1176
  -0.750   0.3370   0.01669   0.00732  -0.0632   0.4870   0.1219
  -0.500   0.3631   0.01652   0.00712  -0.0625   0.4770   0.1273
  -0.250   0.3893   0.01634   0.00682  -0.0618   0.4684   0.1324
   0.000   0.4148   0.01606   0.00660  -0.0611   0.4594   0.1384
   0.250   0.4411   0.01607   0.00649  -0.0605   0.4518   0.1453
   0.500   0.4661   0.01579   0.00631  -0.0597   0.4435   0.1530
   0.750   0.4920   0.01580   0.00624  -0.0590   0.4363   0.1623
   1.000   0.5168   0.01565   0.00620  -0.0582   0.4288   0.1744
   1.250   0.5418   0.01555   0.00615  -0.0574   0.4215   0.1916
   1.500   0.5661   0.01544   0.00622  -0.0565   0.4149   0.2406
   1.750   0.6627   0.01375   0.00642  -0.0704   0.4028   1.0000
   2.000   0.6874   0.01409   0.00656  -0.0696   0.3972   1.0000
   2.250   0.7112   0.01428   0.00673  -0.0685   0.3910   1.0000
   2.500   0.7356   0.01452   0.00686  -0.0676   0.3855   1.0000
   2.750   0.7608   0.01490   0.00705  -0.0669   0.3807   1.0000
   3.000   0.7844   0.01512   0.00728  -0.0659   0.3753   1.0000
   3.250   0.8085   0.01535   0.00747  -0.0649   0.3700   1.0000
   3.500   0.8333   0.01563   0.00763  -0.0641   0.3655   1.0000
   3.750   0.8583   0.01603   0.00792  -0.0634   0.3615   1.0000
   4.000   0.8818   0.01630   0.00823  -0.0624   0.3571   1.0000
   4.250   0.9060   0.01658   0.00849  -0.0616   0.3529   1.0000
   4.500   0.9307   0.01686   0.00869  -0.0608   0.3490   1.0000
   4.750   0.9564   0.01730   0.00899  -0.0603   0.3453   1.0000
   5.000   0.9793   0.01761   0.00937  -0.0592   0.3416   1.0000
   5.250   1.0028   0.01792   0.00971  -0.0583   0.3378   1.0000
   5.500   1.0269   0.01819   0.00996  -0.0575   0.3338   1.0000
   5.750   1.0518   0.01848   0.01015  -0.0568   0.3300   1.0000
   6.000   1.0755   0.01891   0.01054  -0.0560   0.3261   1.0000
   6.250   1.0974   0.01918   0.01091  -0.0549   0.3219   1.0000
   6.500   1.1207   0.01946   0.01119  -0.0540   0.3179   1.0000
   6.750   1.1451   0.01975   0.01142  -0.0533   0.3144   1.0000
   7.000   1.1711   0.02027   0.01181  -0.0529   0.3110   1.0000
   7.250   1.1912   0.02060   0.01229  -0.0516   0.3075   1.0000
   7.500   1.2128   0.02095   0.01270  -0.0505   0.3036   1.0000
   7.750   1.2359   0.02128   0.01304  -0.0496   0.3001   1.0000
   8.000   1.2602   0.02161   0.01331  -0.0490   0.2969   1.0000
   8.250   1.2841   0.02216   0.01381  -0.0484   0.2934   1.0000
   8.500   1.3024   0.02254   0.01436  -0.0469   0.2896   1.0000
   8.750   1.3230   0.02291   0.01478  -0.0457   0.2857   1.0000
   9.000   1.3456   0.02324   0.01509  -0.0449   0.2822   1.0000
   9.250   1.3705   0.02369   0.01545  -0.0445   0.2788   1.0000
   9.500   1.3882   0.02423   0.01612  -0.0430   0.2751   1.0000
   9.750   1.4051   0.02466   0.01666  -0.0413   0.2710   1.0000
  10.000   1.4250   0.02498   0.01699  -0.0401   0.2669   1.0000
  10.250   1.4483   0.02535   0.01728  -0.0395   0.2632   1.0000
  10.500   1.4655   0.02600   0.01801  -0.0381   0.2594   1.0000
  10.750   1.4780   0.02650   0.01866  -0.0359   0.2551   1.0000
  11.000   1.4948   0.02687   0.01906  -0.0343   0.2509   1.0000
  11.250   1.5166   0.02725   0.01934  -0.0336   0.2469   1.0000
  11.500   1.5273   0.02794   0.02016  -0.0313   0.2428   1.0000
  11.750   1.5342   0.02851   0.02087  -0.0285   0.2384   1.0000
  12.000   1.5454   0.02894   0.02131  -0.0261   0.2344   1.0000
  12.250   1.5675   0.02941   0.02165  -0.0255   0.2302   1.0000
  12.500   1.5622   0.03027   0.02272  -0.0213   0.2265   1.0000
  12.750   1.5632   0.03110   0.02366  -0.0183   0.2223   1.0000
  13.000   1.5719   0.03174   0.02431  -0.0163   0.2183   1.0000
  13.250   1.5896   0.03239   0.02486  -0.0154   0.2143   1.0000
  13.500   1.5799   0.03395   0.02667  -0.0124   0.2105   1.0000
  13.750   1.5800   0.03531   0.02813  -0.0106   0.2065   1.0000
  14.000   1.5869   0.03637   0.02920  -0.0094   0.2029   1.0000
  14.250   1.5977   0.03746   0.03024  -0.0085   0.1991   1.0000
  14.500   1.5874   0.03992   0.03293  -0.0072   0.1955   1.0000
  14.750   1.5856   0.04197   0.03509  -0.0064   0.1917   1.0000
  15.000   1.5908   0.04352   0.03664  -0.0059   0.1884   1.0000
  15.250   1.6005   0.04487   0.03794  -0.0052   0.1850   1.0000
  15.500   1.5859   0.04844   0.04174  -0.0051   0.1818   1.0000
  15.750   1.5792   0.05143   0.04484  -0.0052   0.1786   1.0000
  16.000   1.5805   0.05365   0.04710  -0.0051   0.1756   1.0000
  16.250   1.5985   0.05417   0.04750  -0.0044   0.1723   1.0000
  16.500   1.5774   0.05896   0.05252  -0.0053   0.1697   1.0000
  16.750   1.5583   0.06385   0.05760  -0.0064   0.1668   1.0000
  17.000   1.5506   0.06752   0.06136  -0.0073   0.1638   1.0000
  17.250   1.5564   0.06949   0.06332  -0.0074   0.1612   1.0000
  17.500   1.5741   0.06996   0.06369  -0.0066   0.1582   1.0000
  17.750   1.5327   0.07840   0.07244  -0.0099   0.1560   1.0000
  18.000   1.4897   0.08763   0.08193  -0.0137   0.1533   1.0000
  18.250   1.4668   0.09419   0.08863  -0.0163   0.1506   1.0000
  18.500   1.4871   0.09413   0.08851  -0.0156   0.1483   1.0000
  18.750   1.5411   0.08894   0.08310  -0.0119   0.1457   1.0000
  19.000   0.9957   0.20391   0.19900  -0.0730   0.1224   1.0000
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