Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

MUE 139 (mue139-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: MUE 139 (mue139-il)
Reynolds number: 100,000
Max Cl/Cd: 35.33 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mue139-il-100000.txt
Download as CSV file: xf-mue139-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2126   0.09742   0.09278  -0.0251   1.0000   0.1229
  -8.000  -0.2123   0.09529   0.09074  -0.0251   1.0000   0.1260
  -7.750  -0.2314   0.09431   0.08993  -0.0263   1.0000   0.1295
  -7.500  -0.2729   0.09519   0.09109  -0.0238   1.0000   0.1302
  -7.250  -0.2766   0.09143   0.08740  -0.0318   0.9843   0.1317
  -7.000  -0.2306   0.08676   0.08274  -0.0295   0.9812   0.1339
  -6.750  -0.1923   0.08257   0.07854  -0.0343   0.9671   0.1385
  -6.500  -0.1777   0.07649   0.07233  -0.0555   0.9394   0.1474
  -6.250  -0.1346   0.07276   0.06866  -0.0528   0.9287   0.1507
  -5.750  -0.0780   0.06433   0.06002  -0.0672   0.8860   0.1663
  -5.500  -0.0481   0.06160   0.05721  -0.0681   0.8640   0.1718
  -5.250  -0.0416   0.05834   0.05372  -0.0736   0.8385   0.1828
  -5.000  -0.0205   0.05621   0.05156  -0.0715   0.8153   0.1867
  -4.750  -0.0116   0.05384   0.04893  -0.0741   0.7939   0.2007
  -4.500   0.0072   0.05203   0.04709  -0.0712   0.7725   0.2060
  -4.250   0.0191   0.05000   0.04487  -0.0716   0.7528   0.2205
  -4.000   0.0329   0.04843   0.04310  -0.0716   0.7338   0.2370
  -3.750   0.0504   0.04662   0.04127  -0.0691   0.7150   0.2430
  -3.500   0.0656   0.04496   0.03948  -0.0682   0.6975   0.2593
  -3.250   0.0936   0.03377   0.02654  -0.0765   0.6900   0.1493
  -3.000   0.1163   0.03155   0.02389  -0.0755   0.6750   0.1423
  -2.750   0.1379   0.02966   0.02165  -0.0743   0.6593   0.1404
  -2.500   0.1609   0.02834   0.01996  -0.0731   0.6446   0.1421
  -2.250   0.1853   0.02715   0.01837  -0.0720   0.6316   0.1437
  -2.000   0.2107   0.02618   0.01697  -0.0709   0.6191   0.1455
  -1.750   0.2345   0.02510   0.01573  -0.0700   0.6056   0.1492
  -1.500   0.2600   0.02439   0.01492  -0.0692   0.5938   0.1536
  -1.250   0.2864   0.02376   0.01404  -0.0683   0.5825   0.1580
  -1.000   0.3120   0.02343   0.01346  -0.0673   0.5702   0.1634
  -0.750   0.3387   0.02262   0.01261  -0.0667   0.5603   0.1691
  -0.500   0.3645   0.02228   0.01220  -0.0659   0.5489   0.1765
  -0.250   0.3910   0.02187   0.01172  -0.0652   0.5393   0.1842
   0.000   0.4172   0.02156   0.01139  -0.0645   0.5294   0.1934
   0.250   0.4428   0.02130   0.01117  -0.0637   0.5198   0.2045
   0.500   0.4691   0.02106   0.01090  -0.0629   0.5106   0.2185
   0.750   0.4939   0.02095   0.01091  -0.0621   0.5013   0.2377
   1.000   0.5206   0.02080   0.01085  -0.0614   0.4928   0.2714
   1.250   0.6092   0.01886   0.01080  -0.0727   0.4798   1.0000
   1.500   0.6348   0.01923   0.01084  -0.0719   0.4730   1.0000
   1.750   0.6572   0.01973   0.01125  -0.0707   0.4652   1.0000
   2.000   0.6810   0.02013   0.01149  -0.0697   0.4579   1.0000
   2.250   0.7065   0.02061   0.01173  -0.0690   0.4520   1.0000
   2.500   0.7274   0.02117   0.01231  -0.0677   0.4446   1.0000
   2.750   0.7516   0.02164   0.01266  -0.0668   0.4390   1.0000
   3.000   0.7774   0.02223   0.01304  -0.0662   0.4342   1.0000
   3.250   0.7969   0.02291   0.01383  -0.0648   0.4279   1.0000
   3.500   0.8200   0.02345   0.01431  -0.0639   0.4223   1.0000
   3.750   0.8461   0.02395   0.01463  -0.0633   0.4178   1.0000
   4.000   0.8658   0.02478   0.01552  -0.0620   0.4127   1.0000
   4.250   0.8862   0.02556   0.01636  -0.0608   0.4076   1.0000
   4.500   0.9096   0.02616   0.01691  -0.0600   0.4031   1.0000
   4.750   0.9359   0.02673   0.01732  -0.0595   0.3992   1.0000
   5.000   0.9523   0.02776   0.01851  -0.0580   0.3943   1.0000
   5.250   0.9705   0.02871   0.01954  -0.0566   0.3895   1.0000
   5.500   0.9934   0.02936   0.02016  -0.0558   0.3853   1.0000
   5.750   1.0203   0.02987   0.02054  -0.0554   0.3816   1.0000
   6.000   1.0344   0.03111   0.02193  -0.0537   0.3768   1.0000
   6.250   1.0485   0.03226   0.02322  -0.0520   0.3717   1.0000
   6.500   1.0722   0.03276   0.02369  -0.0513   0.3672   1.0000
   6.750   1.1018   0.03305   0.02381  -0.0511   0.3635   1.0000
   7.000   1.1081   0.03474   0.02574  -0.0488   0.3585   1.0000
   7.250   1.1195   0.03601   0.02714  -0.0469   0.3532   1.0000
   7.500   1.1454   0.03633   0.02740  -0.0464   0.3490   1.0000
   7.750   1.1787   0.03642   0.02731  -0.0466   0.3455   1.0000
   8.000   1.1683   0.03908   0.03035  -0.0429   0.3400   1.0000
   8.250   1.1761   0.04054   0.03193  -0.0408   0.3350   1.0000
   8.500   1.2087   0.04033   0.03162  -0.0408   0.3310   1.0000
   8.750   1.2442   0.04030   0.03142  -0.0412   0.3274   1.0000
   9.000   1.1963   0.04518   0.03682  -0.0348   0.3213   1.0000
   9.250   1.2033   0.04654   0.03825  -0.0329   0.3167   1.0000
   9.500   1.2603   0.04473   0.03625  -0.0345   0.3130   1.0000
   9.750   1.2491   0.04741   0.03908  -0.0313   0.3086   1.0000
  10.000   0.7796   0.10606   0.09846  -0.0433   0.2833   1.0000
<< Back to MUE 139 (mue139-il)

Polar data table (+)

Polar graphs


<< Back to MUE 139 (mue139-il)