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MUE 139 (mue139-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MUE 139 (mue139-il)
Reynolds number: 500,000
Max Cl/Cd: 89.2 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mue139-il-500000.txt
Download as CSV file: xf-mue139-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2503   0.09267   0.09045  -0.0267   1.0000   0.0492
  -8.750  -0.2431   0.08939   0.08719  -0.0290   0.9988   0.0504
  -8.250  -0.4011   0.02432   0.01988  -0.0875   0.8690   0.0464
  -8.000  -0.3880   0.02205   0.01704  -0.0859   0.8304   0.0469
  -7.750  -0.3700   0.02072   0.01548  -0.0845   0.8025   0.0475
  -7.500  -0.3482   0.02012   0.01473  -0.0833   0.7807   0.0479
  -7.250  -0.3255   0.01961   0.01408  -0.0822   0.7635   0.0485
  -7.000  -0.3028   0.01904   0.01335  -0.0812   0.7483   0.0491
  -6.750  -0.2797   0.01842   0.01257  -0.0801   0.7340   0.0498
  -6.500  -0.2567   0.01768   0.01164  -0.0791   0.7208   0.0506
  -6.250  -0.2331   0.01706   0.01080  -0.0780   0.7074   0.0515
  -5.750  -0.1856   0.01568   0.00909  -0.0760   0.6791   0.0534
  -5.500  -0.1602   0.01533   0.00869  -0.0752   0.6659   0.0542
  -5.250  -0.1347   0.01504   0.00832  -0.0744   0.6528   0.0551
  -5.000  -0.1091   0.01470   0.00788  -0.0736   0.6391   0.0562
  -4.750  -0.0833   0.01435   0.00741  -0.0729   0.6245   0.0574
  -4.500  -0.0574   0.01408   0.00699  -0.0721   0.6086   0.0585
  -4.250  -0.0326   0.01352   0.00636  -0.0712   0.5913   0.0600
  -4.000  -0.0067   0.01339   0.00617  -0.0705   0.5724   0.0614
  -3.750   0.0192   0.01326   0.00596  -0.0697   0.5531   0.0630
  -3.500   0.0452   0.01312   0.00568  -0.0689   0.5342   0.0648
  -3.250   0.0707   0.01284   0.00527  -0.0681   0.5167   0.0664
  -3.000   0.0963   0.01265   0.00504  -0.0674   0.5012   0.0681
  -2.750   0.1224   0.01260   0.00491  -0.0667   0.4876   0.0700
  -2.500   0.1489   0.01253   0.00476  -0.0660   0.4757   0.0722
  -2.250   0.1751   0.01236   0.00452  -0.0654   0.4653   0.0745
  -2.000   0.2010   0.01226   0.00439  -0.0647   0.4554   0.0768
  -1.750   0.2278   0.01220   0.00430  -0.0641   0.4468   0.0793
  -1.500   0.2545   0.01219   0.00421  -0.0635   0.4386   0.0817
  -1.250   0.2803   0.01199   0.00400  -0.0628   0.4316   0.0848
  -1.000   0.3071   0.01194   0.00395  -0.0623   0.4244   0.0878
  -0.750   0.3334   0.01196   0.00390  -0.0616   0.4174   0.0909
  -0.500   0.3599   0.01180   0.00375  -0.0610   0.4112   0.0945
  -0.250   0.3863   0.01174   0.00370  -0.0604   0.4046   0.0983
   0.000   0.4124   0.01179   0.00368  -0.0598   0.3979   0.1021
   0.250   0.4391   0.01165   0.00357  -0.0592   0.3918   0.1068
   0.500   0.4654   0.01162   0.00354  -0.0586   0.3851   0.1118
   0.750   0.4917   0.01167   0.00354  -0.0580   0.3787   0.1163
   1.000   0.5180   0.01155   0.00347  -0.0574   0.3725   0.1235
   1.250   0.5442   0.01158   0.00347  -0.0568   0.3662   0.1301
   1.500   0.5699   0.01155   0.00346  -0.0561   0.3603   0.1398
   1.750   0.5962   0.01150   0.00346  -0.0555   0.3544   0.1540
   2.000   0.6210   0.01140   0.00349  -0.0547   0.3485   0.2015
   2.250   0.6435   0.01110   0.00363  -0.0537   0.3432   0.3668
   2.500   0.7513   0.00987   0.00391  -0.0706   0.3326   1.0000
   2.750   0.7748   0.01008   0.00401  -0.0695   0.3273   1.0000
   3.000   0.7997   0.01018   0.00410  -0.0687   0.3230   1.0000
   3.250   0.8241   0.01033   0.00420  -0.0677   0.3186   1.0000
   3.500   0.8479   0.01052   0.00431  -0.0667   0.3144   1.0000
   3.750   0.8714   0.01076   0.00447  -0.0657   0.3102   1.0000
   4.000   0.8963   0.01088   0.00460  -0.0648   0.3068   1.0000
   4.250   0.9207   0.01103   0.00472  -0.0640   0.3030   1.0000
   4.500   0.9447   0.01123   0.00487  -0.0630   0.2995   1.0000
   4.750   0.9678   0.01150   0.00505  -0.0620   0.2955   1.0000
   5.000   0.9922   0.01165   0.00521  -0.0611   0.2917   1.0000
   5.250   1.0167   0.01179   0.00534  -0.0603   0.2878   1.0000
   5.500   1.0407   0.01197   0.00550  -0.0594   0.2842   1.0000
   5.750   1.0639   0.01222   0.00569  -0.0584   0.2809   1.0000
   6.000   1.0867   0.01253   0.00595  -0.0573   0.2775   1.0000
   6.250   1.1112   0.01269   0.00614  -0.0565   0.2753   1.0000
   6.500   1.1352   0.01287   0.00634  -0.0557   0.2727   1.0000
   6.750   1.1589   0.01306   0.00653  -0.0548   0.2697   1.0000
   7.000   1.1820   0.01330   0.00675  -0.0539   0.2668   1.0000
   7.250   1.2043   0.01361   0.00701  -0.0528   0.2637   1.0000
   7.500   1.2268   0.01393   0.00732  -0.0518   0.2609   1.0000
   7.750   1.2503   0.01411   0.00755  -0.0509   0.2588   1.0000
   8.000   1.2734   0.01431   0.00778  -0.0500   0.2562   1.0000
   8.250   1.2961   0.01453   0.00802  -0.0490   0.2534   1.0000
   8.500   1.3179   0.01479   0.00827  -0.0480   0.2503   1.0000
   8.750   1.3386   0.01515   0.00859  -0.0468   0.2471   1.0000
   9.000   1.3601   0.01547   0.00893  -0.0457   0.2445   1.0000
   9.250   1.3821   0.01567   0.00919  -0.0446   0.2420   1.0000
   9.500   1.4035   0.01589   0.00946  -0.0435   0.2391   1.0000
   9.750   1.4239   0.01614   0.00973  -0.0423   0.2360   1.0000
  10.000   1.4426   0.01649   0.01005  -0.0408   0.2325   1.0000
  10.250   1.4608   0.01690   0.01046  -0.0393   0.2292   1.0000
  10.500   1.4802   0.01711   0.01075  -0.0379   0.2265   1.0000
  10.750   1.4974   0.01735   0.01105  -0.0362   0.2230   1.0000
  11.000   1.5126   0.01767   0.01138  -0.0341   0.2194   1.0000
  11.250   1.5251   0.01816   0.01183  -0.0319   0.2154   1.0000
  11.500   1.5422   0.01847   0.01222  -0.0303   0.2119   1.0000
  11.750   1.5587   0.01881   0.01263  -0.0288   0.2076   1.0000
  12.000   1.5724   0.01931   0.01313  -0.0270   0.2032   1.0000
  12.250   1.5848   0.01993   0.01376  -0.0252   0.1988   1.0000
  12.500   1.6006   0.02042   0.01432  -0.0239   0.1940   1.0000
  12.750   1.6122   0.02116   0.01508  -0.0223   0.1891   1.0000
  13.000   1.6223   0.02206   0.01599  -0.0208   0.1844   1.0000
  13.250   1.6349   0.02288   0.01687  -0.0196   0.1794   1.0000
  13.500   1.6422   0.02410   0.01809  -0.0183   0.1744   1.0000
  13.750   1.6502   0.02538   0.01941  -0.0172   0.1700   1.0000
  14.000   1.6585   0.02672   0.02081  -0.0163   0.1654   1.0000
  14.250   1.6617   0.02856   0.02266  -0.0155   0.1610   1.0000
  14.500   1.6653   0.03045   0.02460  -0.0148   0.1572   1.0000
  14.750   1.6706   0.03228   0.02649  -0.0143   0.1534   1.0000
  15.000   1.6715   0.03455   0.02880  -0.0140   0.1501   1.0000
  15.250   1.6667   0.03743   0.03170  -0.0137   0.1468   1.0000
  15.500   1.6675   0.03982   0.03417  -0.0134   0.1442   1.0000
  15.750   1.6682   0.04227   0.03672  -0.0133   0.1416   1.0000
  16.000   1.6648   0.04518   0.03970  -0.0134   0.1392   1.0000
  16.250   1.6574   0.04859   0.04315  -0.0136   0.1367   1.0000
  16.500   1.6473   0.05237   0.04695  -0.0139   0.1343   1.0000
  16.750   1.6426   0.05567   0.05035  -0.0144   0.1319   1.0000
  17.000   1.6394   0.05891   0.05369  -0.0149   0.1302   1.0000
  17.250   1.6326   0.06270   0.05757  -0.0157   0.1275   1.0000
  17.500   1.6241   0.06665   0.06157  -0.0165   0.1255   1.0000
  17.750   1.6144   0.07076   0.06571  -0.0174   0.1234   1.0000
  18.000   1.6065   0.07459   0.06957  -0.0182   0.1208   1.0000
  18.250   1.6003   0.07851   0.07361  -0.0193   0.1191   1.0000
  18.500   1.5940   0.08240   0.07760  -0.0203   0.1175   1.0000
  18.750   1.5850   0.08672   0.08199  -0.0216   0.1153   1.0000
  19.000   1.5774   0.09076   0.08608  -0.0228   0.1133   1.0000
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