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MUE 139 (mue139-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MUE 139 (mue139-il)
Reynolds number: 200,000
Max Cl/Cd: 63.52 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mue139-il-200000-n5.txt
Download as CSV file: xf-mue139-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2692   0.09604   0.09234  -0.0286   1.0000   0.0430
  -9.250  -0.2709   0.09231   0.08865  -0.0299   1.0000   0.0428
  -9.000  -0.2732   0.08866   0.08505  -0.0311   1.0000   0.0428
  -8.750  -0.2670   0.08436   0.08078  -0.0343   0.9737   0.0429
  -8.500  -0.2325   0.07821   0.07453  -0.0456   0.9171   0.0436
  -8.250  -0.2001   0.07099   0.06714  -0.0588   0.8698   0.0447
  -7.750  -0.3393   0.03093   0.02537  -0.0841   0.8034   0.0472
  -7.500  -0.3170   0.03033   0.02462  -0.0835   0.7811   0.0477
  -7.250  -0.2973   0.02931   0.02341  -0.0826   0.7628   0.0483
  -7.000  -0.2801   0.02769   0.02148  -0.0816   0.7472   0.0491
  -6.750  -0.2635   0.02576   0.01916  -0.0804   0.7327   0.0501
  -6.500  -0.2464   0.02375   0.01669  -0.0792   0.7191   0.0512
  -6.250  -0.2275   0.02195   0.01436  -0.0779   0.7063   0.0524
  -5.750  -0.1790   0.02117   0.01346  -0.0762   0.6794   0.0540
  -5.500  -0.1547   0.02072   0.01288  -0.0754   0.6658   0.0551
  -5.250  -0.1307   0.02009   0.01205  -0.0744   0.6518   0.0564
  -5.000  -0.1070   0.01931   0.01099  -0.0734   0.6368   0.0579
  -4.750  -0.0826   0.01867   0.01014  -0.0725   0.6203   0.0591
  -4.500  -0.0576   0.01835   0.00978  -0.0717   0.6031   0.0601
  -4.250  -0.0325   0.01806   0.00939  -0.0709   0.5859   0.0614
  -4.000  -0.0073   0.01774   0.00891  -0.0700   0.5687   0.0632
  -3.750   0.0180   0.01733   0.00828  -0.0692   0.5519   0.0654
  -3.500   0.0432   0.01704   0.00792  -0.0684   0.5356   0.0669
  -3.250   0.0686   0.01684   0.00764  -0.0676   0.5207   0.0684
  -3.000   0.0940   0.01663   0.00731  -0.0668   0.5068   0.0704
  -2.750   0.1199   0.01641   0.00692  -0.0661   0.4934   0.0730
  -2.500   0.1454   0.01620   0.00667  -0.0654   0.4814   0.0750
  -2.250   0.1709   0.01608   0.00648  -0.0646   0.4705   0.0772
  -2.000   0.1970   0.01593   0.00625  -0.0639   0.4603   0.0800
  -1.750   0.2227   0.01579   0.00599  -0.0632   0.4518   0.0828
  -1.500   0.2487   0.01564   0.00586  -0.0626   0.4435   0.0855
  -1.250   0.2744   0.01557   0.00571  -0.0619   0.4360   0.0885
  -1.000   0.3008   0.01547   0.00556  -0.0612   0.4288   0.0920
  -0.750   0.3264   0.01534   0.00543  -0.0605   0.4214   0.0953
  -0.500   0.3521   0.01530   0.00535  -0.0598   0.4146   0.0991
  -0.250   0.3784   0.01524   0.00525  -0.0592   0.4074   0.1033
   0.000   0.4036   0.01517   0.00517  -0.0585   0.4007   0.1077
   0.250   0.4296   0.01513   0.00513  -0.0578   0.3947   0.1126
   0.500   0.4556   0.01510   0.00508  -0.0572   0.3883   0.1179
   0.750   0.4809   0.01507   0.00506  -0.0565   0.3826   0.1244
   1.000   0.5069   0.01509   0.00504  -0.0559   0.3771   0.1314
   1.250   0.5326   0.01504   0.00505  -0.0552   0.3712   0.1410
   1.500   0.5578   0.01504   0.00506  -0.0545   0.3655   0.1539
   1.750   0.5829   0.01501   0.00510  -0.0538   0.3602   0.1786
   2.000   0.6066   0.01477   0.00523  -0.0529   0.3543   0.2811
   2.250   0.6299   0.01462   0.00531  -0.0519   0.3489   0.3748
   2.750   0.7483   0.01371   0.00573  -0.0645   0.3358   1.0000
   3.000   0.7721   0.01392   0.00584  -0.0635   0.3313   1.0000
   3.250   0.7956   0.01416   0.00596  -0.0625   0.3275   1.0000
   3.500   0.8200   0.01435   0.00613  -0.0616   0.3231   1.0000
   3.750   0.8439   0.01455   0.00629  -0.0607   0.3185   1.0000
   4.000   0.8675   0.01479   0.00645  -0.0597   0.3144   1.0000
   4.250   0.8907   0.01506   0.00662  -0.0586   0.3111   1.0000
   4.500   0.9149   0.01529   0.00685  -0.0578   0.3077   1.0000
   4.750   0.9388   0.01553   0.00708  -0.0569   0.3041   1.0000
   5.000   0.9623   0.01578   0.00729  -0.0559   0.3004   1.0000
   5.250   0.9854   0.01605   0.00750  -0.0550   0.2971   1.0000
   5.500   1.0083   0.01637   0.00774  -0.0540   0.2941   1.0000
   5.750   1.0320   0.01663   0.00803  -0.0531   0.2909   1.0000
   6.000   1.0552   0.01689   0.00830  -0.0522   0.2871   1.0000
   6.250   1.0778   0.01716   0.00855  -0.0511   0.2829   1.0000
   6.500   1.0997   0.01747   0.00879  -0.0501   0.2790   1.0000
   6.750   1.1222   0.01778   0.00910  -0.0491   0.2756   1.0000
   7.000   1.1448   0.01807   0.00943  -0.0481   0.2720   1.0000
   7.250   1.1668   0.01837   0.00975  -0.0471   0.2686   1.0000
   7.500   1.1884   0.01871   0.01007  -0.0460   0.2654   1.0000
   7.750   1.2096   0.01909   0.01040  -0.0449   0.2625   1.0000
   8.000   1.2310   0.01944   0.01078  -0.0438   0.2597   1.0000
   8.250   1.2522   0.01978   0.01119  -0.0427   0.2565   1.0000
   8.500   1.2727   0.02013   0.01158  -0.0415   0.2532   1.0000
   8.750   1.2924   0.02050   0.01196  -0.0403   0.2499   1.0000
   9.000   1.3116   0.02092   0.01235  -0.0389   0.2470   1.0000
   9.250   1.3307   0.02135   0.01280  -0.0376   0.2442   1.0000
   9.500   1.3493   0.02174   0.01330  -0.0362   0.2411   1.0000
   9.750   1.3670   0.02216   0.01378  -0.0347   0.2378   1.0000
  10.000   1.3829   0.02259   0.01424  -0.0330   0.2344   1.0000
  10.250   1.3967   0.02306   0.01469  -0.0309   0.2314   1.0000
  10.500   1.4102   0.02356   0.01524  -0.0289   0.2283   1.0000
  10.750   1.4235   0.02407   0.01586  -0.0269   0.2248   1.0000
  11.000   1.4362   0.02462   0.01648  -0.0250   0.2214   1.0000
  11.250   1.4476   0.02523   0.01712  -0.0230   0.2180   1.0000
  11.500   1.4580   0.02594   0.01782  -0.0211   0.2149   1.0000
  11.750   1.4692   0.02669   0.01870  -0.0194   0.2110   1.0000
  12.000   1.4793   0.02752   0.01963  -0.0178   0.2070   1.0000
  12.250   1.4875   0.02848   0.02063  -0.0162   0.2032   1.0000
  12.500   1.4944   0.02959   0.02175  -0.0148   0.1998   1.0000
  12.750   1.5029   0.03076   0.02306  -0.0136   0.1956   1.0000
  13.000   1.5091   0.03212   0.02451  -0.0126   0.1912   1.0000
  13.250   1.5130   0.03372   0.02613  -0.0117   0.1873   1.0000
  13.500   1.5173   0.03544   0.02793  -0.0109   0.1834   1.0000
  13.750   1.5206   0.03733   0.02993  -0.0104   0.1790   1.0000
  14.000   1.5215   0.03950   0.03216  -0.0100   0.1751   1.0000
  14.250   1.5201   0.04195   0.03463  -0.0098   0.1714   1.0000
  14.500   1.5200   0.04445   0.03725  -0.0097   0.1674   1.0000
  14.750   1.5167   0.04729   0.04017  -0.0097   0.1636   1.0000
  15.000   1.5111   0.05046   0.04337  -0.0100   0.1603   1.0000
  15.250   1.5055   0.05372   0.04671  -0.0104   0.1572   1.0000
  15.500   1.4994   0.05722   0.05033  -0.0109   0.1538   1.0000
  15.750   1.4920   0.06096   0.05415  -0.0117   0.1507   1.0000
  16.000   1.4836   0.06487   0.05810  -0.0126   0.1478   1.0000
  16.250   1.4761   0.06875   0.06201  -0.0135   0.1452   1.0000
  16.500   1.4679   0.07292   0.06632  -0.0146   0.1426   1.0000
  16.750   1.4587   0.07726   0.07077  -0.0159   0.1398   1.0000
  17.000   1.4506   0.08147   0.07503  -0.0171   0.1372   1.0000
  17.250   1.4450   0.08531   0.07889  -0.0182   0.1349   1.0000
  17.500   1.4416   0.08883   0.08242  -0.0192   0.1325   1.0000
  17.750   1.4299   0.09381   0.08756  -0.0209   0.1302   1.0000
  18.000   1.4182   0.09884   0.09271  -0.0228   0.1276   1.0000
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