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LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL113.6 AIRFOIL (c141b-il)
Reynolds number: 100,000
Max Cl/Cd: 45.14 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141b-il-100000.txt
Download as CSV file: xf-c141b-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5422   0.09402   0.08872  -0.0368   1.0000   0.1764
  -9.500  -0.5391   0.09123   0.08595  -0.0352   1.0000   0.1801
  -9.250  -0.8253   0.06109   0.05479  -0.0335   1.0000   0.0845
  -9.000  -0.8275   0.05726   0.05086  -0.0307   1.0000   0.0836
  -8.750  -0.8331   0.05361   0.04699  -0.0273   1.0000   0.0829
  -8.500  -0.8384   0.05011   0.04315  -0.0235   1.0000   0.0828
  -8.250  -0.8405   0.04688   0.03949  -0.0198   1.0000   0.0834
  -8.000  -0.8392   0.04394   0.03606  -0.0163   1.0000   0.0843
  -7.750  -0.8339   0.04141   0.03299  -0.0130   1.0000   0.0851
  -7.500  -0.8221   0.03804   0.02943  -0.0112   1.0000   0.0866
  -7.250  -0.8050   0.03649   0.02792  -0.0099   1.0000   0.0897
  -7.000  -0.7896   0.03486   0.02603  -0.0080   1.0000   0.0932
  -6.750  -0.7734   0.03302   0.02374  -0.0060   1.0000   0.0962
  -6.500  -0.7549   0.03111   0.02156  -0.0046   1.0000   0.0999
  -6.250  -0.7345   0.02992   0.02036  -0.0036   1.0000   0.1046
  -6.000  -0.7136   0.02873   0.01889  -0.0023   1.0000   0.1095
  -5.750  -0.6918   0.02735   0.01743  -0.0014   1.0000   0.1151
  -5.500  -0.6701   0.02641   0.01644  -0.0004   1.0000   0.1215
  -5.250  -0.6478   0.02535   0.01527   0.0005   1.0000   0.1287
  -5.000  -0.6260   0.02453   0.01447   0.0015   1.0000   0.1374
  -4.750  -0.6040   0.02360   0.01360   0.0024   1.0000   0.1471
  -4.500  -0.5823   0.02283   0.01284   0.0034   1.0000   0.1595
  -4.250  -0.5611   0.02207   0.01218   0.0044   1.0000   0.1752
  -4.000  -0.5405   0.02128   0.01158   0.0054   1.0000   0.1959
  -3.750  -0.5202   0.02044   0.01101   0.0064   1.0000   0.2281
  -3.500  -0.5007   0.01930   0.01044   0.0075   1.0000   0.2965
  -3.250  -0.4866   0.01754   0.01036   0.0100   1.0000   0.5624
  -3.000  -0.4716   0.01744   0.01080   0.0138   1.0000   0.7097
  -2.750  -0.4552   0.01763   0.01114   0.0172   1.0000   0.7773
  -2.500  -0.4383   0.01795   0.01152   0.0205   1.0000   0.8275
  -2.250  -0.4190   0.01839   0.01195   0.0234   1.0000   0.8702
  -2.000  -0.3926   0.01898   0.01248   0.0247   1.0000   0.9087
  -1.750  -0.3477   0.01986   0.01323   0.0222   1.0000   0.9412
  -1.500  -0.2738   0.02102   0.01418   0.0136   1.0000   0.9639
  -1.250  -0.1856   0.02206   0.01502   0.0017   1.0000   0.9841
  -1.000  -0.1002   0.02267   0.01546  -0.0103   1.0000   1.0000
  -0.750  -0.1046   0.02233   0.01509  -0.0064   1.0000   1.0000
  -0.500  -0.1094   0.02201   0.01474  -0.0024   1.0000   1.0000
  -0.250  -0.1135   0.02174   0.01443   0.0016   1.0000   1.0000
   0.000  -0.1086   0.02164   0.01428   0.0041   0.9990   1.0000
   0.250  -0.0663   0.02212   0.01469  -0.0001   0.9909   1.0000
   0.500  -0.0249   0.02264   0.01516  -0.0040   0.9830   1.0000
   0.750   0.0113   0.02300   0.01548  -0.0068   0.9735   1.0000
   1.000   0.0454   0.02336   0.01581  -0.0091   0.9635   1.0000
   1.250   0.0834   0.02380   0.01623  -0.0121   0.9545   1.0000
   1.500   0.1204   0.02416   0.01659  -0.0147   0.9446   1.0000
   1.750   0.1519   0.02444   0.01687  -0.0161   0.9330   1.0000
   2.000   0.1909   0.02475   0.01721  -0.0188   0.9225   1.0000
   2.250   0.2403   0.02495   0.01746  -0.0231   0.9123   1.0000
   2.500   0.2850   0.02484   0.01741  -0.0262   0.8975   1.0000
   2.750   0.3422   0.02436   0.01703  -0.0309   0.8817   1.0000
   3.000   0.3954   0.02372   0.01651  -0.0347   0.8663   1.0000
   3.250   0.4459   0.02298   0.01590  -0.0379   0.8515   1.0000
   3.500   0.5012   0.02194   0.01502  -0.0415   0.8367   1.0000
   3.750   0.5597   0.02054   0.01381  -0.0453   0.8212   1.0000
   4.000   0.6100   0.01903   0.01248  -0.0473   0.8024   1.0000
   4.250   0.6400   0.01799   0.01155  -0.0458   0.7762   1.0000
   4.500   0.6761   0.01685   0.01049  -0.0453   0.7378   1.0000
   4.750   0.7186   0.01592   0.00941  -0.0457   0.6564   1.0000
   5.000   0.7369   0.01639   0.00892  -0.0422   0.4763   1.0000
   5.250   0.7303   0.01789   0.00937  -0.0356   0.3330   1.0000
   5.500   0.7310   0.01925   0.01008  -0.0307   0.2620   1.0000
   5.750   0.7388   0.02038   0.01085  -0.0271   0.2224   1.0000
   6.000   0.7508   0.02143   0.01162  -0.0243   0.1955   1.0000
   6.250   0.7672   0.02246   0.01248  -0.0223   0.1749   1.0000
   6.500   0.7860   0.02349   0.01339  -0.0207   0.1585   1.0000
   6.750   0.8079   0.02465   0.01442  -0.0197   0.1452   1.0000
   7.000   0.8298   0.02569   0.01539  -0.0187   0.1339   1.0000
   7.250   0.8534   0.02689   0.01668  -0.0179   0.1245   1.0000
   7.500   0.8803   0.02842   0.01810  -0.0180   0.1162   1.0000
   7.750   0.9015   0.02957   0.01944  -0.0167   0.1095   1.0000
   8.000   0.9286   0.03142   0.02116  -0.0170   0.1031   1.0000
   8.250   0.9469   0.03278   0.02286  -0.0150   0.0985   1.0000
   8.500   0.9669   0.03415   0.02432  -0.0138   0.0938   1.0000
   8.750   0.9887   0.03649   0.02672  -0.0132   0.0899   1.0000
   9.000   1.0007   0.03838   0.02906  -0.0104   0.0874   1.0000
   9.250   1.0128   0.04036   0.03135  -0.0079   0.0844   1.0000
   9.500   1.0296   0.04206   0.03314  -0.0065   0.0814   1.0000
   9.750   1.0462   0.04479   0.03591  -0.0054   0.0792   1.0000
  10.000   1.0514   0.04821   0.03967  -0.0025   0.0784   1.0000
  10.250   1.0498   0.05107   0.04298   0.0015   0.0779   1.0000
  10.500   1.0441   0.05414   0.04646   0.0056   0.0774   1.0000
  10.750   1.0346   0.05739   0.05008   0.0099   0.0771   1.0000
  11.000   1.0215   0.06077   0.05378   0.0141   0.0770   1.0000
  11.250   1.0045   0.06412   0.05739   0.0184   0.0770   1.0000
  11.500   0.9852   0.06762   0.06110   0.0224   0.0772   1.0000
  11.750   0.9664   0.07152   0.06517   0.0253   0.0776   1.0000
  12.000   0.9522   0.07597   0.06974   0.0271   0.0781   1.0000
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