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LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)
Reynolds number: 50,000
Max Cl/Cd: 30.92 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141d-il-50000-n5.txt
Download as CSV file: xf-c141d-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5053   0.10057   0.09266  -0.0395   1.0000   0.0605
  -9.750  -0.5123   0.09586   0.08803  -0.0413   1.0000   0.0602
  -9.500  -0.5220   0.09086   0.08309  -0.0435   1.0000   0.0599
  -9.250  -0.5371   0.08533   0.07764  -0.0463   1.0000   0.0592
  -9.000  -0.5600   0.08053   0.07290  -0.0471   1.0000   0.0584
  -8.750  -0.5843   0.07629   0.06867  -0.0459   1.0000   0.0577
  -8.500  -0.6040   0.07212   0.06444  -0.0445   1.0000   0.0574
  -8.250  -0.6195   0.06822   0.06042  -0.0426   1.0000   0.0573
  -8.000  -0.6305   0.06452   0.05657  -0.0405   1.0000   0.0574
  -7.750  -0.6378   0.06092   0.05276  -0.0382   1.0000   0.0577
  -7.500  -0.6417   0.05735   0.04894  -0.0359   1.0000   0.0580
  -7.250  -0.6423   0.05385   0.04513  -0.0336   1.0000   0.0584
  -7.000  -0.6394   0.05052   0.04145  -0.0314   1.0000   0.0591
  -6.750  -0.6336   0.04741   0.03794  -0.0292   1.0000   0.0606
  -6.500  -0.6260   0.04418   0.03411  -0.0270   1.0000   0.0627
  -6.250  -0.6130   0.04191   0.03160  -0.0253   1.0000   0.0649
  -6.000  -0.5977   0.04002   0.02952  -0.0238   1.0000   0.0672
  -5.750  -0.5814   0.03793   0.02704  -0.0222   1.0000   0.0706
  -5.500  -0.5635   0.03584   0.02450  -0.0208   1.0000   0.0745
  -5.250  -0.5443   0.03441   0.02300  -0.0197   1.0000   0.0785
  -5.000  -0.5235   0.03289   0.02105  -0.0184   1.0000   0.0841
  -4.750  -0.5024   0.03148   0.01958  -0.0175   1.0000   0.0891
  -4.500  -0.4803   0.03032   0.01823  -0.0165   1.0000   0.0957
  -4.250  -0.4576   0.02917   0.01701  -0.0156   1.0000   0.1022
  -4.000  -0.4344   0.02827   0.01596  -0.0147   1.0000   0.1101
  -3.750  -0.4114   0.02740   0.01511  -0.0139   1.0000   0.1184
  -3.500  -0.3879   0.02667   0.01426  -0.0130   1.0000   0.1283
  -3.250  -0.3649   0.02599   0.01355  -0.0123   1.0000   0.1402
  -3.000  -0.3420   0.02531   0.01289  -0.0116   1.0000   0.1543
  -2.750  -0.3203   0.02467   0.01228  -0.0108   1.0000   0.1733
  -2.500  -0.2986   0.02395   0.01175  -0.0101   1.0000   0.2027
  -2.250  -0.2769   0.02291   0.01123  -0.0097   1.0000   0.2775
  -2.000  -0.2634   0.02107   0.01135  -0.0065   1.0000   0.6281
  -1.750  -0.2374   0.02103   0.01187  -0.0035   1.0000   0.8526
  -1.500  -0.1449   0.02171   0.01224  -0.0151   1.0000   0.9999
  -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  -0.1067   0.02181   0.01177  -0.0094   0.9984   1.0000
  -0.500  -0.0723   0.02212   0.01188  -0.0115   0.9922   1.0000
  -0.250  -0.0382   0.02245   0.01204  -0.0136   0.9856   1.0000
   0.000  -0.0055   0.02277   0.01220  -0.0154   0.9786   1.0000
   0.250   0.0300   0.02316   0.01247  -0.0176   0.9724   1.0000
   0.500   0.0602   0.02345   0.01267  -0.0188   0.9642   1.0000
   0.750   0.0953   0.02385   0.01298  -0.0209   0.9576   1.0000
   1.000   0.1254   0.02415   0.01324  -0.0220   0.9488   1.0000
   1.250   0.1581   0.02450   0.01356  -0.0236   0.9409   1.0000
   1.500   0.1910   0.02485   0.01389  -0.0251   0.9325   1.0000
   1.750   0.2206   0.02516   0.01421  -0.0260   0.9230   1.0000
   2.000   0.2578   0.02551   0.01459  -0.0283   0.9152   1.0000
   2.250   0.2851   0.02578   0.01490  -0.0286   0.9038   1.0000
   2.500   0.3181   0.02603   0.01522  -0.0298   0.8930   1.0000
   2.750   0.3580   0.02616   0.01545  -0.0321   0.8820   1.0000
   3.000   0.3974   0.02608   0.01549  -0.0339   0.8673   1.0000
   3.250   0.4305   0.02581   0.01535  -0.0342   0.8468   1.0000
   3.500   0.4694   0.02528   0.01497  -0.0350   0.8250   1.0000
   3.750   0.5153   0.02426   0.01414  -0.0363   0.8003   1.0000
   4.000   0.5480   0.02336   0.01336  -0.0351   0.7680   1.0000
   4.250   0.5735   0.02274   0.01286  -0.0329   0.7306   1.0000
   4.500   0.6039   0.02215   0.01237  -0.0316   0.6869   1.0000
   4.750   0.6343   0.02169   0.01188  -0.0302   0.6220   1.0000
   5.000   0.6675   0.02159   0.01126  -0.0291   0.4942   1.0000
   5.250   0.6799   0.02272   0.01149  -0.0257   0.3624   1.0000
   5.500   0.6886   0.02410   0.01227  -0.0226   0.2846   1.0000
   5.750   0.7011   0.02539   0.01317  -0.0203   0.2380   1.0000
   6.000   0.7167   0.02659   0.01410  -0.0185   0.2083   1.0000
   6.250   0.7357   0.02767   0.01511  -0.0171   0.1862   1.0000
   6.500   0.7567   0.02873   0.01612  -0.0161   0.1692   1.0000
   6.750   0.7802   0.02980   0.01716  -0.0155   0.1551   1.0000
   7.000   0.8058   0.03091   0.01824  -0.0152   0.1432   1.0000
   7.250   0.8314   0.03204   0.01938  -0.0149   0.1324   1.0000
   7.500   0.8587   0.03327   0.02075  -0.0148   0.1225   1.0000
   7.750   0.8848   0.03464   0.02212  -0.0147   0.1143   1.0000
   8.000   0.9093   0.03603   0.02366  -0.0143   0.1065   1.0000
   8.250   0.9340   0.03770   0.02543  -0.0140   0.1001   1.0000
   8.500   0.9556   0.03933   0.02726  -0.0132   0.0939   1.0000
   8.750   0.9775   0.04117   0.02915  -0.0126   0.0892   1.0000
   9.000   0.9943   0.04327   0.03168  -0.0111   0.0843   1.0000
   9.250   1.0113   0.04510   0.03364  -0.0100   0.0803   1.0000
   9.500   1.0266   0.04740   0.03612  -0.0087   0.0773   1.0000
   9.750   1.0332   0.05013   0.03938  -0.0062   0.0741   1.0000
  10.000   1.0408   0.05256   0.04211  -0.0041   0.0713   1.0000
  10.250   1.0493   0.05489   0.04461  -0.0022   0.0692   1.0000
  10.500   1.0580   0.05734   0.04714  -0.0007   0.0675   1.0000
  10.750   1.0458   0.06090   0.05122   0.0031   0.0663   1.0000
  11.000   1.0298   0.06438   0.05509   0.0068   0.0653   1.0000
  11.250   1.0103   0.06797   0.05899   0.0102   0.0647   1.0000
  11.500   0.9880   0.07202   0.06330   0.0126   0.0642   1.0000
  11.750   0.9622   0.07678   0.06831   0.0137   0.0641   1.0000
  12.000   0.9326   0.08261   0.07434   0.0132   0.0643   1.0000
  12.250   0.8998   0.08994   0.08184   0.0105   0.0648   1.0000
  12.500   0.8661   0.09915   0.09115   0.0053   0.0655   1.0000
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