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LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il)
Reynolds number: 100,000
Max Cl/Cd: 42.52 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141b-il-100000-n5.txt
Download as CSV file: xf-c141b-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL113.6 AIRFOIL                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6717   0.08316   0.07727  -0.0604   1.0000   0.0393
 -12.500  -0.7131   0.07293   0.06691  -0.0669   1.0000   0.0388
 -12.250  -0.7485   0.06612   0.05994  -0.0697   1.0000   0.0386
 -12.000  -0.7806   0.06121   0.05485  -0.0696   1.0000   0.0385
 -11.750  -0.8105   0.05752   0.05100  -0.0672   1.0000   0.0385
 -11.500  -0.8391   0.05473   0.04803  -0.0628   1.0000   0.0385
 -11.250  -0.8672   0.05262   0.04575  -0.0569   1.0000   0.0386
 -11.000  -0.8909   0.05028   0.04317  -0.0510   1.0000   0.0389
 -10.750  -0.9095   0.04770   0.04027  -0.0456   1.0000   0.0392
 -10.500  -0.9233   0.04509   0.03726  -0.0405   1.0000   0.0397
 -10.250  -0.9213   0.04352   0.03562  -0.0374   1.0000   0.0402
 -10.000  -0.9177   0.04209   0.03409  -0.0343   1.0000   0.0409
  -9.750  -0.9128   0.04075   0.03262  -0.0313   1.0000   0.0418
  -9.500  -0.9073   0.03933   0.03101  -0.0284   1.0000   0.0430
  -9.250  -0.9010   0.03768   0.02908  -0.0254   1.0000   0.0446
  -9.000  -0.8937   0.03581   0.02677  -0.0225   1.0000   0.0463
  -8.750  -0.8813   0.03454   0.02545  -0.0205   1.0000   0.0475
  -8.500  -0.8679   0.03347   0.02430  -0.0185   1.0000   0.0489
  -8.250  -0.8539   0.03241   0.02309  -0.0165   1.0000   0.0508
  -8.000  -0.8388   0.03122   0.02163  -0.0146   1.0000   0.0533
  -7.750  -0.8226   0.03011   0.02041  -0.0129   1.0000   0.0554
  -7.500  -0.8060   0.02928   0.01956  -0.0113   1.0000   0.0575
  -7.250  -0.7885   0.02845   0.01860  -0.0098   1.0000   0.0605
  -7.000  -0.7697   0.02755   0.01750  -0.0084   0.9999   0.0636
  -6.750  -0.7424   0.02669   0.01668  -0.0090   0.9976   0.0669
  -6.500  -0.7141   0.02597   0.01585  -0.0096   0.9952   0.0714
  -6.250  -0.6863   0.02518   0.01501  -0.0101   0.9929   0.0757
  -6.000  -0.6595   0.02453   0.01434  -0.0104   0.9901   0.0808
  -5.750  -0.6317   0.02389   0.01364  -0.0108   0.9874   0.0867
  -5.500  -0.6028   0.02333   0.01308  -0.0115   0.9848   0.0934
  -5.250  -0.5751   0.02276   0.01251  -0.0120   0.9822   0.1013
  -5.000  -0.5490   0.02228   0.01199  -0.0120   0.9787   0.1108
  -4.750  -0.5213   0.02177   0.01154  -0.0125   0.9755   0.1226
  -4.500  -0.4917   0.02131   0.01112  -0.0133   0.9727   0.1381
  -4.250  -0.4635   0.02086   0.01076  -0.0139   0.9697   0.1587
  -4.000  -0.4389   0.02037   0.01041  -0.0137   0.9655   0.1866
  -3.750  -0.4114   0.01983   0.01010  -0.0142   0.9620   0.2313
  -3.500  -0.3827   0.01914   0.00984  -0.0150   0.9590   0.3112
  -3.250  -0.3586   0.01835   0.00970  -0.0148   0.9557   0.4385
  -3.000  -0.3378   0.01785   0.00976  -0.0134   0.9509   0.5591
  -2.750  -0.3106   0.01772   0.00992  -0.0129   0.9470   0.6438
  -2.500  -0.2795   0.01774   0.01006  -0.0131   0.9439   0.7012
  -2.250  -0.2538   0.01778   0.01014  -0.0124   0.9393   0.7415
  -2.000  -0.2277   0.01785   0.01025  -0.0116   0.9342   0.7746
  -1.750  -0.1961   0.01798   0.01042  -0.0118   0.9305   0.8053
  -1.500  -0.1608   0.01818   0.01062  -0.0128   0.9278   0.8336
  -1.250  -0.1351   0.01840   0.01087  -0.0117   0.9221   0.8629
  -1.000  -0.1017   0.01871   0.01117  -0.0121   0.9179   0.8925
  -0.750  -0.0594   0.01899   0.01142  -0.0146   0.9151   0.9107
  -0.500  -0.0159   0.01913   0.01151  -0.0178   0.9126   0.9207
  -0.250   0.0200   0.01926   0.01160  -0.0196   0.9076   0.9306
   0.000   0.0551   0.01934   0.01166  -0.0213   0.9021   0.9414
   0.250   0.1013   0.01941   0.01171  -0.0252   0.8990   0.9474
   0.500   0.1460   0.01943   0.01171  -0.0288   0.8963   0.9549
   0.750   0.1842   0.01951   0.01182  -0.0313   0.8896   0.9617
   1.000   0.2262   0.01950   0.01183  -0.0344   0.8847   0.9687
   1.250   0.2744   0.01941   0.01178  -0.0387   0.8815   0.9730
   1.500   0.3147   0.01937   0.01179  -0.0416   0.8748   0.9793
   1.750   0.3580   0.01920   0.01169  -0.0448   0.8682   0.9846
   2.000   0.4039   0.01867   0.01122  -0.0479   0.8568   0.9881
   2.250   0.4488   0.01788   0.01048  -0.0503   0.8391   0.9916
   2.500   0.4903   0.01728   0.00995  -0.0523   0.8203   0.9960
   2.750   0.5289   0.01681   0.00955  -0.0541   0.8010   1.0000
   3.000   0.5453   0.01656   0.00934  -0.0516   0.7778   1.0000
   3.250   0.5711   0.01617   0.00895  -0.0506   0.7512   1.0000
   3.500   0.5999   0.01580   0.00854  -0.0501   0.7148   1.0000
   3.750   0.6348   0.01549   0.00808  -0.0506   0.6603   1.0000
   4.000   0.6612   0.01555   0.00781  -0.0497   0.5833   1.0000
   4.250   0.6760   0.01602   0.00778  -0.0468   0.4861   1.0000
   4.750   0.6887   0.01763   0.00835  -0.0389   0.3095   1.0000
   5.000   0.6972   0.01837   0.00876  -0.0355   0.2532   1.0000
   5.250   0.7074   0.01905   0.00918  -0.0325   0.2132   1.0000
   5.500   0.7191   0.01966   0.00962  -0.0296   0.1841   1.0000
   5.750   0.7309   0.02028   0.01010  -0.0268   0.1623   1.0000
   6.000   0.7438   0.02086   0.01060  -0.0242   0.1452   1.0000
   6.250   0.7565   0.02147   0.01112  -0.0216   0.1314   1.0000
   6.500   0.7702   0.02205   0.01168  -0.0191   0.1198   1.0000
   6.750   0.7842   0.02266   0.01229  -0.0167   0.1101   1.0000
   7.000   0.7974   0.02336   0.01291  -0.0143   0.1023   1.0000
   7.250   0.8127   0.02400   0.01359  -0.0121   0.0948   1.0000
   7.500   0.8270   0.02477   0.01431  -0.0100   0.0889   1.0000
   7.750   0.8431   0.02548   0.01509  -0.0080   0.0831   1.0000
   8.000   0.8570   0.02634   0.01587  -0.0060   0.0787   1.0000
   8.250   0.8747   0.02711   0.01676  -0.0043   0.0738   1.0000
   8.500   0.8907   0.02795   0.01761  -0.0026   0.0700   1.0000
   8.750   0.9074   0.02893   0.01860  -0.0011   0.0665   1.0000
   9.000   0.9256   0.02987   0.01968   0.0003   0.0628   1.0000
   9.250   0.9421   0.03083   0.02065   0.0018   0.0600   1.0000
   9.500   0.9594   0.03198   0.02181   0.0031   0.0574   1.0000
   9.750   0.9773   0.03313   0.02318   0.0044   0.0545   1.0000
  10.000   0.9934   0.03427   0.02441   0.0058   0.0522   1.0000
  10.250   1.0089   0.03543   0.02557   0.0072   0.0504   1.0000
  10.500   1.0245   0.03692   0.02723   0.0086   0.0485   1.0000
  10.750   1.0374   0.03842   0.02899   0.0104   0.0464   1.0000
  11.000   1.0488   0.03983   0.03056   0.0122   0.0449   1.0000
  11.250   1.0600   0.04130   0.03213   0.0140   0.0437   1.0000
  11.500   1.0715   0.04285   0.03372   0.0155   0.0428   1.0000
  11.750   1.0766   0.04501   0.03616   0.0178   0.0418   1.0000
  12.000   1.0761   0.04738   0.03891   0.0205   0.0407   1.0000
  12.250   1.0738   0.04975   0.04157   0.0231   0.0398   1.0000
  12.500   1.0704   0.05210   0.04415   0.0255   0.0389   1.0000
  12.750   1.0661   0.05451   0.04676   0.0275   0.0382   1.0000
  13.000   1.0614   0.05700   0.04942   0.0293   0.0376   1.0000
  13.250   1.0554   0.05972   0.05230   0.0307   0.0371   1.0000
  13.500   1.0471   0.06282   0.05557   0.0318   0.0368   1.0000
  13.750   1.0361   0.06636   0.05929   0.0324   0.0365   1.0000
  14.000   1.0218   0.07048   0.06359   0.0324   0.0363   1.0000
  14.250   1.0017   0.07561   0.06892   0.0315   0.0362   1.0000
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