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LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il)
Reynolds number: 50,000
Max Cl/Cd: 32.59 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141f-il-50000-n5.txt
Download as CSV file: xf-c141f-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL958.89 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4295   0.11327   0.10538  -0.0294   1.0000   0.1314
  -9.000  -0.4537   0.11185   0.10410  -0.0315   1.0000   0.1342
  -8.750  -0.4774   0.11004   0.10244  -0.0325   1.0000   0.1347
  -8.500  -0.4550   0.10496   0.09736  -0.0303   1.0000   0.1365
  -8.250  -0.4464   0.10166   0.09409  -0.0286   1.0000   0.1387
  -8.000  -0.4483   0.09892   0.09142  -0.0275   1.0000   0.1408
  -7.750  -0.4564   0.09640   0.08898  -0.0264   1.0000   0.1430
  -7.500  -0.4692   0.09384   0.08653  -0.0258   1.0000   0.1454
  -7.000  -0.4963   0.08745   0.08027  -0.0275   1.0000   0.1529
  -6.500  -0.5071   0.07165   0.06375  -0.0351   1.0000   0.0806
  -6.250  -0.5002   0.06853   0.06062  -0.0340   1.0000   0.0799
  -6.000  -0.4934   0.06529   0.05732  -0.0331   1.0000   0.0787
  -5.750  -0.4860   0.06188   0.05377  -0.0325   1.0000   0.0774
  -5.500  -0.4768   0.05839   0.05008  -0.0321   1.0000   0.0763
  -5.250  -0.4655   0.05514   0.04658  -0.0317   1.0000   0.0762
  -5.000  -0.4522   0.05214   0.04331  -0.0313   1.0000   0.0769
  -4.750  -0.4370   0.04928   0.04013  -0.0308   1.0000   0.0775
  -4.500  -0.4199   0.04656   0.03708  -0.0303   1.0000   0.0777
  -4.250  -0.4012   0.04400   0.03419  -0.0298   1.0000   0.0776
  -4.000  -0.3811   0.04169   0.03152  -0.0293   1.0000   0.0781
  -3.750  -0.3594   0.03962   0.02896  -0.0288   1.0000   0.0798
  -3.500  -0.3370   0.03775   0.02670  -0.0283   1.0000   0.0812
  -3.250  -0.3147   0.03618   0.02499  -0.0279   1.0000   0.0824
  -3.000  -0.2913   0.03478   0.02337  -0.0275   1.0000   0.0836
  -2.750  -0.2677   0.03363   0.02205  -0.0271   1.0000   0.0861
  -2.500  -0.2434   0.03256   0.02072  -0.0266   1.0000   0.0889
  -2.250  -0.2186   0.03156   0.01942  -0.0261   1.0000   0.0910
  -2.000  -0.1944   0.03062   0.01834  -0.0256   1.0000   0.0933
  -1.750  -0.1711   0.02990   0.01765  -0.0251   1.0000   0.0970
  -1.500  -0.1472   0.02930   0.01695  -0.0245   1.0000   0.1008
  -1.250  -0.1128   0.02878   0.01625  -0.0256   0.9962   0.1052
  -1.000  -0.0788   0.02825   0.01580  -0.0270   0.9922   0.1114
  -0.750  -0.0436   0.02794   0.01536  -0.0285   0.9875   0.1183
  -0.500  -0.0082   0.02758   0.01506  -0.0302   0.9833   0.1276
  -0.250   0.0251   0.02728   0.01476  -0.0316   0.9776   0.1387
   0.000   0.0621   0.02701   0.01457  -0.0338   0.9730   0.1572
   0.250   0.0945   0.02658   0.01440  -0.0353   0.9668   0.1914
   0.500   0.1255   0.02399   0.01458  -0.0351   0.9622   1.0000
   0.750   0.1588   0.02439   0.01466  -0.0364   0.9550   1.0000
   1.000   0.1931   0.02480   0.01486  -0.0380   0.9475   1.0000
   1.250   0.2250   0.02519   0.01510  -0.0391   0.9393   1.0000
   1.500   0.2605   0.02558   0.01539  -0.0410   0.9311   1.0000
   1.750   0.2946   0.02581   0.01555  -0.0423   0.9184   1.0000
   2.000   0.3381   0.02574   0.01544  -0.0448   0.9009   1.0000
   2.250   0.3858   0.02525   0.01493  -0.0474   0.8785   1.0000
   2.500   0.4228   0.02479   0.01448  -0.0481   0.8560   1.0000
   2.750   0.4583   0.02452   0.01425  -0.0487   0.8393   1.0000
   3.000   0.4919   0.02429   0.01408  -0.0490   0.8234   1.0000
   3.250   0.5254   0.02395   0.01382  -0.0491   0.8057   1.0000
   3.500   0.5581   0.02354   0.01350  -0.0488   0.7859   1.0000
   3.750   0.5940   0.02298   0.01304  -0.0488   0.7626   1.0000
   4.000   0.6203   0.02263   0.01279  -0.0472   0.7297   1.0000
   4.250   0.6501   0.02206   0.01222  -0.0457   0.6779   1.0000
   4.500   0.6889   0.02143   0.01124  -0.0451   0.5736   1.0000
   4.750   0.7159   0.02197   0.01086  -0.0434   0.4377   1.0000
   5.000   0.7304   0.02309   0.01134  -0.0408   0.3633   1.0000
   5.250   0.7464   0.02418   0.01204  -0.0389   0.3189   1.0000
   5.500   0.7649   0.02517   0.01282  -0.0374   0.2867   1.0000
   5.750   0.7844   0.02617   0.01360  -0.0361   0.2613   1.0000
   6.000   0.8060   0.02712   0.01446  -0.0352   0.2388   1.0000
   6.250   0.8288   0.02809   0.01537  -0.0344   0.2195   1.0000
   6.500   0.8535   0.02908   0.01630  -0.0339   0.2031   1.0000
   6.750   0.8803   0.03011   0.01725  -0.0338   0.1896   1.0000
   7.000   0.9070   0.03111   0.01829  -0.0336   0.1776   1.0000
   7.250   0.9347   0.03219   0.01945  -0.0336   0.1674   1.0000
   7.500   0.9612   0.03330   0.02047  -0.0334   0.1596   1.0000
   7.750   0.9869   0.03447   0.02188  -0.0331   0.1512   1.0000
   8.000   1.0116   0.03563   0.02297  -0.0327   0.1450   1.0000
   8.250   1.0346   0.03699   0.02459  -0.0320   0.1378   1.0000
   8.500   1.0564   0.03814   0.02573  -0.0313   0.1319   1.0000
   8.750   1.0759   0.03964   0.02752  -0.0302   0.1252   1.0000
   9.000   1.0950   0.04081   0.02870  -0.0291   0.1195   1.0000
   9.250   1.1112   0.04249   0.03066  -0.0277   0.1134   1.0000
   9.500   1.1279   0.04378   0.03201  -0.0264   0.1080   1.0000
   9.750   1.1414   0.04570   0.03420  -0.0247   0.1029   1.0000
  10.000   1.1543   0.04742   0.03610  -0.0230   0.0980   1.0000
  10.250   1.1674   0.04923   0.03799  -0.0215   0.0940   1.0000
  10.500   1.1710   0.05181   0.04102  -0.0189   0.0898   1.0000
  10.750   1.1811   0.05363   0.04291  -0.0171   0.0864   1.0000
  11.000   1.1836   0.05617   0.04569  -0.0147   0.0835   1.0000
  11.250   1.1728   0.05941   0.04937  -0.0110   0.0811   1.0000
  11.500   1.1644   0.06230   0.05253  -0.0079   0.0791   1.0000
  11.750   1.1611   0.06479   0.05515  -0.0056   0.0771   1.0000
  12.000   1.1642   0.06697   0.05734  -0.0039   0.0753   1.0000
  12.250   1.1354   0.07166   0.06241  -0.0013   0.0747   1.0000
  12.500   1.1043   0.07712   0.06820  -0.0002   0.0743   1.0000
  12.750   1.0697   0.08375   0.07511  -0.0010   0.0743   1.0000
  13.000   1.0313   0.09215   0.08373  -0.0042   0.0746   1.0000
  13.250   0.9891   0.10318   0.09491  -0.0104   0.0751   1.0000
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