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LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)
Reynolds number: 50,000
Max Cl/Cd: 31.51 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141d-il-50000.txt
Download as CSV file: xf-c141d-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL610.61 AIRFOIL                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4478   0.10695   0.09940  -0.0174   1.0000   0.3020
  -8.750  -0.4516   0.10425   0.09678  -0.0165   1.0000   0.3153
  -8.500  -0.4541   0.10165   0.09426  -0.0152   1.0000   0.3312
  -8.250  -0.4429   0.09848   0.09111  -0.0132   1.0000   0.3512
  -8.000  -0.4381   0.09580   0.08849  -0.0112   1.0000   0.3726
  -7.750  -0.4489   0.09414   0.08693  -0.0086   1.0000   0.3945
  -7.500  -0.4415   0.09091   0.08374  -0.0063   1.0000   0.4159
  -7.250  -0.4273   0.08791   0.08075  -0.0040   1.0000   0.4423
  -7.000  -0.4157   0.08497   0.07784  -0.0013   1.0000   0.4722
  -6.750  -0.4130   0.08258   0.07552   0.0019   1.0000   0.5022
  -6.250  -0.6078   0.06157   0.05399  -0.0239   1.0000   0.1931
  -6.000  -0.5967   0.05596   0.04809  -0.0236   1.0000   0.1714
  -5.750  -0.5903   0.05097   0.04240  -0.0228   1.0000   0.1571
  -5.500  -0.5773   0.04723   0.03840  -0.0215   1.0000   0.1538
  -5.250  -0.5629   0.04378   0.03450  -0.0202   1.0000   0.1519
  -5.000  -0.5463   0.04086   0.03111  -0.0189   1.0000   0.1536
  -4.750  -0.5271   0.03815   0.02787  -0.0176   1.0000   0.1557
  -4.500  -0.5063   0.03575   0.02493  -0.0165   1.0000   0.1604
  -4.250  -0.4842   0.03365   0.02278  -0.0156   1.0000   0.1675
  -4.000  -0.4603   0.03201   0.02056  -0.0146   1.0000   0.1757
  -3.750  -0.4363   0.03020   0.01880  -0.0140   1.0000   0.1862
  -3.500  -0.4106   0.02870   0.01713  -0.0134   1.0000   0.1979
  -3.250  -0.3845   0.02743   0.01578  -0.0127   1.0000   0.2132
  -3.000  -0.3578   0.02626   0.01465  -0.0121   1.0000   0.2327
  -2.750  -0.3303   0.02520   0.01362  -0.0117   1.0000   0.2605
  -2.500  -0.1595   0.02258   0.01393  -0.0282   1.0000   1.0000
  -2.250  -0.1586   0.02226   0.01340  -0.0246   1.0000   1.0000
  -2.000  -0.1562   0.02201   0.01293  -0.0212   1.0000   1.0000
  -1.750  -0.1516   0.02183   0.01255  -0.0180   1.0000   1.0000
  -1.500  -0.1448   0.02172   0.01224  -0.0151   1.0000   1.0000
  -1.250  -0.1359   0.02167   0.01201  -0.0125   1.0000   1.0000
  -1.000  -0.1249   0.02169   0.01184  -0.0103   1.0000   1.0000
  -0.750  -0.1119   0.02177   0.01174  -0.0084   1.0000   1.0000
  -0.500  -0.0973   0.02191   0.01172  -0.0067   1.0000   1.0000
  -0.250  -0.0815   0.02210   0.01176  -0.0054   1.0000   1.0000
   0.000  -0.0648   0.02233   0.01186  -0.0041   1.0000   1.0000
   0.250  -0.0474   0.02261   0.01202  -0.0031   1.0000   1.0000
   0.500  -0.0295   0.02293   0.01224  -0.0022   1.0000   1.0000
   0.750  -0.0112   0.02330   0.01251  -0.0014   1.0000   1.0000
   1.000   0.0072   0.02370   0.01284  -0.0006   1.0000   1.0000
   1.250   0.0258   0.02415   0.01323   0.0000   1.0000   1.0000
   1.500   0.0445   0.02464   0.01368   0.0006   1.0000   1.0000
   1.750   0.0632   0.02517   0.01418   0.0011   1.0000   1.0000
   2.000   0.0818   0.02575   0.01474   0.0015   1.0000   1.0000
   2.250   0.1003   0.02638   0.01537   0.0019   1.0000   1.0000
   2.500   0.1186   0.02706   0.01606   0.0022   1.0000   1.0000
   2.750   0.1367   0.02780   0.01682   0.0025   1.0000   1.0000
   3.000   0.1545   0.02860   0.01765   0.0026   1.0000   1.0000
   3.250   0.1720   0.02946   0.01857   0.0028   1.0000   1.0000
   3.500   0.1890   0.03040   0.01957   0.0028   1.0000   1.0000
   3.750   0.2502   0.03229   0.02163  -0.0055   0.9788   1.0000
   4.000   0.3306   0.03395   0.02355  -0.0162   0.9432   1.0000
   4.250   0.3941   0.03453   0.02439  -0.0227   0.9064   1.0000
   4.500   0.4786   0.03361   0.02386  -0.0300   0.8585   1.0000
   4.750   0.5595   0.03121   0.02191  -0.0345   0.8124   1.0000
   5.000   0.6358   0.02743   0.01868  -0.0360   0.7626   1.0000
   5.250   0.7029   0.02231   0.01376  -0.0320   0.6128   1.0000
   5.500   0.7219   0.02418   0.01334  -0.0267   0.3674   1.0000
   5.750   0.7489   0.02628   0.01477  -0.0263   0.3035   1.0000
   6.000   0.7828   0.02806   0.01632  -0.0270   0.2661   1.0000
   6.250   0.8172   0.02993   0.01792  -0.0279   0.2407   1.0000
   6.500   0.8456   0.03171   0.01976  -0.0277   0.2217   1.0000
   6.750   0.8727   0.03368   0.02177  -0.0274   0.2066   1.0000
   7.000   0.8990   0.03581   0.02388  -0.0271   0.1934   1.0000
   7.250   0.9176   0.03778   0.02627  -0.0253   0.1831   1.0000
   7.500   0.9391   0.04031   0.02894  -0.0242   0.1745   1.0000
   7.750   0.9548   0.04266   0.03169  -0.0222   0.1668   1.0000
   8.000   0.9749   0.04566   0.03472  -0.0212   0.1606   1.0000
   8.250   0.9806   0.04853   0.03822  -0.0180   0.1566   1.0000
   8.500   0.9874   0.05167   0.04180  -0.0152   0.1531   1.0000
   8.750   0.9936   0.05506   0.04553  -0.0128   0.1507   1.0000
   9.000   1.0134   0.05872   0.04908  -0.0123   0.1459   1.0000
   9.250   1.0081   0.06257   0.05340  -0.0090   0.1455   1.0000
   9.500   1.0059   0.06695   0.05810  -0.0064   0.1458   1.0000
   9.750   0.9529   0.07222   0.06414  -0.0008   0.1524   1.0000
  10.000   0.9252   0.07749   0.06962   0.0017   0.1561   1.0000
  10.250   0.9099   0.08266   0.07487   0.0030   0.1591   1.0000
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