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LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL761.11 AIRFOIL (c141e-il)
Reynolds number: 100,000
Max Cl/Cd: 49.24 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141e-il-100000.txt
Download as CSV file: xf-c141e-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL761.11 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  -0.4636   0.10657   0.10100  -0.0318   1.0000   0.1170
  -9.500  -0.4899   0.10377   0.09832  -0.0356   1.0000   0.1207
  -9.250  -0.5320   0.10085   0.09556  -0.0397   1.0000   0.1214
  -9.000  -0.5054   0.09587   0.09057  -0.0360   1.0000   0.1237
  -8.750  -0.4861   0.09332   0.08800  -0.0328   1.0000   0.1271
  -8.500  -0.4908   0.09064   0.08538  -0.0319   1.0000   0.1309
  -8.250  -0.5131   0.08777   0.08261  -0.0317   1.0000   0.1337
  -8.000  -0.5488   0.08460   0.07952  -0.0322   1.0000   0.1357
  -7.500  -0.5758   0.07713   0.07207  -0.0304   1.0000   0.1407
  -7.250  -0.5655   0.07505   0.07005  -0.0274   1.0000   0.1454
  -7.000  -0.6035   0.07297   0.06756  -0.0285   1.0000   0.1541
  -6.500  -0.5806   0.06561   0.06051  -0.0238   1.0000   0.1618
  -6.250  -0.5905   0.06222   0.05685  -0.0236   1.0000   0.1731
  -6.000  -0.5785   0.05955   0.05428  -0.0213   1.0000   0.1773
  -5.750  -0.5771   0.05667   0.05122  -0.0205   1.0000   0.1907
  -5.500  -0.5711   0.05451   0.04889  -0.0192   1.0000   0.2062
  -5.250  -0.5575   0.05193   0.04648  -0.0169   1.0000   0.2136
  -5.000  -0.5277   0.03797   0.03017  -0.0202   1.0000   0.1043
  -4.750  -0.5080   0.03492   0.02681  -0.0193   1.0000   0.1015
  -4.500  -0.4866   0.03268   0.02418  -0.0184   1.0000   0.1020
  -4.250  -0.4634   0.03075   0.02186  -0.0176   1.0000   0.1030
  -4.000  -0.4392   0.02898   0.01971  -0.0169   1.0000   0.1037
  -3.750  -0.4151   0.02789   0.01821  -0.0160   1.0000   0.1062
  -3.500  -0.3910   0.02616   0.01642  -0.0158   1.0000   0.1102
  -3.250  -0.3670   0.02516   0.01534  -0.0152   1.0000   0.1140
  -3.000  -0.3428   0.02440   0.01439  -0.0145   1.0000   0.1194
  -2.750  -0.3183   0.02339   0.01336  -0.0140   1.0000   0.1257
  -2.500  -0.2943   0.02274   0.01270  -0.0135   1.0000   0.1332
  -2.250  -0.2700   0.02201   0.01201  -0.0131   1.0000   0.1427
  -2.000  -0.2461   0.02159   0.01156  -0.0125   1.0000   0.1542
  -1.750  -0.2219   0.02095   0.01111  -0.0122   1.0000   0.1690
  -1.500  -0.1978   0.02045   0.01078  -0.0119   1.0000   0.1886
  -1.250  -0.1731   0.01996   0.01053  -0.0117   1.0000   0.2210
  -1.000  -0.1326   0.01739   0.01107  -0.0116   1.0000   0.9971
  -0.750  -0.1134   0.01761   0.01101  -0.0106   1.0000   1.0000
  -0.500  -0.0940   0.01788   0.01109  -0.0098   1.0000   1.0000
  -0.250  -0.0742   0.01820   0.01125  -0.0091   1.0000   1.0000
   0.000  -0.0541   0.01855   0.01148  -0.0085   1.0000   1.0000
   0.250  -0.0161   0.01914   0.01193  -0.0114   0.9951   1.0000
   0.500   0.0250   0.01973   0.01241  -0.0148   0.9876   1.0000
   0.750   0.0657   0.02033   0.01292  -0.0181   0.9800   1.0000
   1.000   0.1082   0.02096   0.01348  -0.0217   0.9728   1.0000
   1.250   0.1432   0.02140   0.01389  -0.0239   0.9631   1.0000
   1.500   0.1823   0.02190   0.01436  -0.0267   0.9541   1.0000
   1.750   0.2329   0.02229   0.01476  -0.0313   0.9428   1.0000
   2.000   0.2834   0.02215   0.01463  -0.0352   0.9228   1.0000
   2.250   0.3354   0.02189   0.01442  -0.0392   0.9060   1.0000
   2.500   0.3847   0.02177   0.01436  -0.0429   0.8961   1.0000
   2.750   0.4257   0.02158   0.01426  -0.0450   0.8839   1.0000
   3.000   0.4678   0.02115   0.01393  -0.0469   0.8698   1.0000
   3.250   0.5286   0.01980   0.01274  -0.0509   0.8530   1.0000
   3.500   0.5877   0.01815   0.01124  -0.0542   0.8354   1.0000
   3.750   0.6232   0.01726   0.01047  -0.0538   0.8143   1.0000
   4.000   0.6606   0.01629   0.00962  -0.0537   0.7881   1.0000
   4.250   0.6927   0.01553   0.00893  -0.0525   0.7504   1.0000
   4.500   0.7236   0.01495   0.00828  -0.0511   0.6834   1.0000
   4.750   0.7475   0.01518   0.00772  -0.0483   0.5164   1.0000
   5.000   0.7488   0.01683   0.00816  -0.0430   0.3498   1.0000
   5.250   0.7565   0.01836   0.00899  -0.0394   0.2689   1.0000
   5.500   0.7699   0.01966   0.00985  -0.0368   0.2224   1.0000
   5.750   0.7870   0.02081   0.01069  -0.0350   0.1921   1.0000
   6.000   0.8068   0.02176   0.01157  -0.0335   0.1688   1.0000
   6.250   0.8275   0.02278   0.01246  -0.0323   0.1509   1.0000
   6.500   0.8494   0.02386   0.01347  -0.0312   0.1361   1.0000
   6.750   0.8729   0.02507   0.01462  -0.0304   0.1240   1.0000
   7.000   0.8989   0.02656   0.01597  -0.0302   0.1150   1.0000
   7.250   0.9229   0.02774   0.01724  -0.0295   0.1070   1.0000
   7.500   0.9502   0.02956   0.01905  -0.0294   0.1012   1.0000
   7.750   0.9751   0.03117   0.02087  -0.0287   0.0968   1.0000
   8.000   0.9991   0.03278   0.02250  -0.0283   0.0926   1.0000
   8.250   1.0217   0.03510   0.02500  -0.0276   0.0893   1.0000
   8.500   1.0398   0.03718   0.02750  -0.0258   0.0872   1.0000
   8.750   1.0561   0.03959   0.03030  -0.0240   0.0856   1.0000
   9.000   1.0704   0.04200   0.03304  -0.0220   0.0839   1.0000
   9.250   1.0851   0.04421   0.03547  -0.0203   0.0819   1.0000
   9.500   1.1027   0.04661   0.03792  -0.0193   0.0800   1.0000
   9.750   1.1113   0.04990   0.04153  -0.0171   0.0796   1.0000
  10.000   1.1084   0.05355   0.04573  -0.0133   0.0802   1.0000
  10.250   1.0768   0.05952   0.05256  -0.0068   0.0832   1.0000
  10.500   1.0548   0.06463   0.05809  -0.0025   0.0853   1.0000
  10.750   1.0329   0.06907   0.06278   0.0013   0.0869   1.0000
  11.000   1.0136   0.07341   0.06729   0.0041   0.0882   1.0000
  11.250   1.0016   0.07799   0.07196   0.0056   0.0893   1.0000
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