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LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il)
Reynolds number: 50,000
Max Cl/Cd: 29.32 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141b-il-50000.txt
Download as CSV file: xf-c141b-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4492   0.10544   0.09768  -0.0145   1.0000   0.3913
  -9.000  -0.6164   0.08488   0.07758  -0.0358   1.0000   0.2027
  -8.750  -0.7228   0.07624   0.06882  -0.0334   1.0000   0.1735
  -8.500  -0.7144   0.07194   0.06450  -0.0320   1.0000   0.1692
  -8.250  -0.7718   0.06593   0.05788  -0.0271   1.0000   0.1572
  -8.000  -0.7715   0.06197   0.05373  -0.0247   1.0000   0.1562
  -7.750  -0.7744   0.05823   0.04972  -0.0219   1.0000   0.1559
  -7.500  -0.7755   0.05464   0.04576  -0.0190   1.0000   0.1560
  -7.250  -0.7733   0.05117   0.04187  -0.0162   1.0000   0.1562
  -7.000  -0.7679   0.04795   0.03814  -0.0135   1.0000   0.1568
  -6.750  -0.7516   0.04522   0.03552  -0.0123   1.0000   0.1616
  -6.500  -0.7388   0.04277   0.03277  -0.0102   1.0000   0.1659
  -6.250  -0.7250   0.04024   0.02974  -0.0082   1.0000   0.1697
  -6.000  -0.7086   0.03791   0.02707  -0.0065   1.0000   0.1757
  -5.750  -0.6886   0.03606   0.02509  -0.0053   1.0000   0.1832
  -5.500  -0.6685   0.03416   0.02287  -0.0040   1.0000   0.1919
  -5.250  -0.6467   0.03263   0.02115  -0.0028   1.0000   0.2031
  -5.000  -0.6235   0.03109   0.01960  -0.0020   1.0000   0.2164
  -4.750  -0.5993   0.02968   0.01817  -0.0012   1.0000   0.2332
  -4.500  -0.5748   0.02838   0.01687  -0.0003   1.0000   0.2559
  -4.250  -0.5501   0.02709   0.01574   0.0005   1.0000   0.2876
  -4.000  -0.5260   0.02562   0.01472   0.0013   1.0000   0.3388
  -3.750  -0.5096   0.02360   0.01389   0.0038   1.0000   0.4565
  -3.500  -0.5064   0.02307   0.01496   0.0132   1.0000   0.7235
  -3.250  -0.4830   0.02460   0.01650   0.0201   1.0000   0.8402
  -3.000  -0.3085   0.02895   0.01989   0.0012   1.0000   0.9405
  -2.750  -0.1050   0.02912   0.01919  -0.0318   1.0000   1.0000
  -2.500  -0.1044   0.02858   0.01856  -0.0290   1.0000   1.0000
  -2.250  -0.1038   0.02810   0.01801  -0.0262   1.0000   1.0000
  -2.000  -0.1033   0.02766   0.01750  -0.0231   1.0000   1.0000
  -1.750  -0.1029   0.02726   0.01704  -0.0200   1.0000   1.0000
  -1.500  -0.1028   0.02689   0.01662  -0.0167   1.0000   1.0000
  -1.250  -0.1029   0.02656   0.01623  -0.0134   1.0000   1.0000
  -1.000  -0.1030   0.02626   0.01588  -0.0099   1.0000   1.0000
  -0.750  -0.1029   0.02600   0.01556  -0.0065   1.0000   1.0000
  -0.500  -0.1020   0.02579   0.01530  -0.0031   1.0000   1.0000
  -0.250  -0.0997   0.02565   0.01509   0.0002   1.0000   1.0000
   0.000  -0.0953   0.02558   0.01496   0.0031   1.0000   1.0000
   0.250  -0.0888   0.02560   0.01490   0.0057   1.0000   1.0000
   0.500  -0.0806   0.02570   0.01493   0.0080   1.0000   1.0000
   0.750  -0.0705   0.02587   0.01503   0.0100   1.0000   1.0000
   1.000  -0.0588   0.02612   0.01522   0.0117   1.0000   1.0000
   1.250  -0.0458   0.02644   0.01549   0.0131   1.0000   1.0000
   1.500  -0.0318   0.02682   0.01583   0.0144   1.0000   1.0000
   1.750  -0.0171   0.02726   0.01625   0.0154   1.0000   1.0000
   2.000  -0.0019   0.02776   0.01673   0.0163   1.0000   1.0000
   2.250   0.0137   0.02832   0.01729   0.0171   1.0000   1.0000
   2.500   0.0294   0.02894   0.01791   0.0177   1.0000   1.0000
   2.750   0.0452   0.02962   0.01860   0.0182   1.0000   1.0000
   3.000   0.0610   0.03036   0.01937   0.0187   1.0000   1.0000
   3.250   0.0766   0.03117   0.02022   0.0190   1.0000   1.0000
   3.500   0.0921   0.03205   0.02115   0.0193   1.0000   1.0000
   3.750   0.1612   0.03434   0.02361   0.0094   0.9750   1.0000
   4.000   0.2345   0.03622   0.02570  -0.0004   0.9432   1.0000
   4.250   0.2971   0.03717   0.02688  -0.0072   0.9094   1.0000
   4.500   0.3561   0.03744   0.02740  -0.0123   0.8742   1.0000
   4.750   0.4210   0.03694   0.02723  -0.0172   0.8377   1.0000
   5.000   0.5076   0.03477   0.02553  -0.0231   0.7995   1.0000
   5.250   0.5697   0.03189   0.02307  -0.0240   0.7564   1.0000
   5.500   0.6627   0.02589   0.01766  -0.0252   0.6838   1.0000
   5.750   0.7145   0.02437   0.01452  -0.0215   0.4255   1.0000
   6.000   0.7295   0.02647   0.01566  -0.0187   0.3353   1.0000
   6.250   0.7615   0.02845   0.01716  -0.0192   0.2798   1.0000
   6.500   0.7973   0.03039   0.01878  -0.0204   0.2445   1.0000
   6.750   0.8277   0.03227   0.02064  -0.0206   0.2209   1.0000
   7.000   0.8548   0.03419   0.02259  -0.0203   0.2038   1.0000
   7.250   0.8800   0.03626   0.02469  -0.0197   0.1907   1.0000
   7.500   0.9035   0.03831   0.02678  -0.0189   0.1794   1.0000
   7.750   0.9184   0.04058   0.02947  -0.0166   0.1721   1.0000
   8.000   0.9395   0.04287   0.03178  -0.0155   0.1642   1.0000
   8.250   0.9491   0.04551   0.03483  -0.0127   0.1593   1.0000
   8.500   0.9556   0.04827   0.03804  -0.0094   0.1560   1.0000
   8.750   0.9631   0.05100   0.04108  -0.0066   0.1521   1.0000
   9.000   0.9842   0.05429   0.04422  -0.0062   0.1470   1.0000
   9.250   0.9815   0.05754   0.04794  -0.0023   0.1462   1.0000
   9.500   0.9760   0.06112   0.05191   0.0014   0.1460   1.0000
   9.750   0.9674   0.06487   0.05600   0.0051   0.1460   1.0000
  10.000   0.9565   0.06880   0.06022   0.0085   0.1461   1.0000
  10.250   0.9447   0.07294   0.06458   0.0115   0.1465   1.0000
  10.500   0.9307   0.07719   0.06905   0.0143   0.1475   1.0000
  10.750   0.8291   0.08430   0.07650   0.0192   0.1596   1.0000
  11.000   0.8212   0.08986   0.08211   0.0190   0.1616   1.0000
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