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LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)
Reynolds number: 100,000
Max Cl/Cd: 44.52 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141d-il-100000-n5.txt
Download as CSV file: xf-c141d-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL610.61 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5246   0.09258   0.08695  -0.0419   1.0000   0.0333
 -10.000  -0.5370   0.08663   0.08107  -0.0446   1.0000   0.0333
  -9.750  -0.5554   0.07959   0.07410  -0.0486   1.0000   0.0330
  -9.500  -0.5881   0.07175   0.06627  -0.0526   1.0000   0.0323
  -9.250  -0.6283   0.06661   0.06108  -0.0504   1.0000   0.0317
  -9.000  -0.6588   0.06171   0.05605  -0.0475   1.0000   0.0315
  -8.750  -0.6786   0.05773   0.05189  -0.0443   1.0000   0.0316
  -8.500  -0.6918   0.05411   0.04806  -0.0411   1.0000   0.0320
  -8.250  -0.7010   0.05046   0.04415  -0.0380   1.0000   0.0324
  -8.000  -0.7071   0.04666   0.03999  -0.0348   1.0000   0.0330
  -7.750  -0.7097   0.04275   0.03562  -0.0317   1.0000   0.0336
  -7.500  -0.7077   0.03895   0.03128  -0.0288   1.0000   0.0341
  -7.250  -0.7011   0.03533   0.02700  -0.0261   1.0000   0.0349
  -7.000  -0.6872   0.03356   0.02504  -0.0244   1.0000   0.0356
  -6.750  -0.6713   0.03217   0.02349  -0.0228   1.0000   0.0366
  -6.500  -0.6545   0.03080   0.02188  -0.0213   1.0000   0.0383
  -6.250  -0.6363   0.02891   0.01951  -0.0198   1.0000   0.0408
  -6.000  -0.6175   0.02811   0.01871  -0.0187   1.0000   0.0426
  -5.500  -0.5615   0.02564   0.01581  -0.0194   0.9961   0.0484
  -5.250  -0.5307   0.02495   0.01504  -0.0205   0.9936   0.0526
  -5.000  -0.5010   0.02412   0.01412  -0.0212   0.9907   0.0570
  -4.750  -0.4700   0.02348   0.01332  -0.0221   0.9877   0.0627
  -4.500  -0.4384   0.02287   0.01275  -0.0233   0.9850   0.0683
  -4.250  -0.4082   0.02224   0.01201  -0.0240   0.9820   0.0747
  -4.000  -0.3789   0.02166   0.01145  -0.0247   0.9783   0.0812
  -3.750  -0.3479   0.02106   0.01085  -0.0256   0.9752   0.0885
  -3.500  -0.3151   0.02059   0.01034  -0.0269   0.9725   0.0974
  -3.250  -0.2880   0.02007   0.00989  -0.0271   0.9680   0.1065
  -3.000  -0.2583   0.01964   0.00951  -0.0278   0.9640   0.1187
  -2.750  -0.2256   0.01925   0.00917  -0.0291   0.9607   0.1366
  -2.500  -0.1951   0.01881   0.00887  -0.0300   0.9570   0.1658
  -2.250  -0.1688   0.01817   0.00862  -0.0302   0.9519   0.2380
  -2.000  -0.1428   0.01679   0.00853  -0.0305   0.9487   0.5130
  -1.750  -0.1157   0.01629   0.00880  -0.0295   0.9457   0.7170
  -1.500  -0.0900   0.01626   0.00900  -0.0280   0.9409   0.8057
  -1.250  -0.0570   0.01641   0.00921  -0.0282   0.9367   0.8713
  -1.000  -0.0094   0.01671   0.00950  -0.0313   0.9351   0.9337
  -0.750   0.0727   0.01716   0.00986  -0.0419   0.9394   0.9858
  -0.500   0.1320   0.01723   0.00983  -0.0487   0.9385   1.0000
  -0.250   0.1629   0.01717   0.00970  -0.0498   0.9327   1.0000
   0.000   0.1891   0.01713   0.00962  -0.0500   0.9255   1.0000
   0.250   0.2174   0.01710   0.00954  -0.0505   0.9185   1.0000
   0.500   0.2552   0.01704   0.00946  -0.0527   0.9147   1.0000
   0.750   0.2731   0.01706   0.00945  -0.0510   0.9042   1.0000
   1.000   0.3104   0.01699   0.00938  -0.0530   0.8998   1.0000
   1.250   0.3306   0.01701   0.00941  -0.0517   0.8897   1.0000
   1.750   0.3930   0.01673   0.00918  -0.0527   0.8727   1.0000
   2.000   0.4300   0.01619   0.00867  -0.0536   0.8575   1.0000
   2.250   0.4675   0.01553   0.00803  -0.0543   0.8383   1.0000
   2.500   0.4979   0.01505   0.00756  -0.0538   0.8149   1.0000
   2.750   0.5257   0.01469   0.00719  -0.0528   0.7872   1.0000
   3.000   0.5501   0.01452   0.00701  -0.0515   0.7592   1.0000
   3.250   0.5782   0.01434   0.00682  -0.0509   0.7267   1.0000
   3.500   0.6071   0.01423   0.00661  -0.0503   0.6819   1.0000
   3.750   0.6345   0.01429   0.00643  -0.0495   0.6147   1.0000
   4.000   0.6549   0.01471   0.00638  -0.0474   0.5167   1.0000
   4.250   0.6659   0.01558   0.00659  -0.0440   0.3994   1.0000
   4.500   0.6758   0.01658   0.00701  -0.0407   0.3039   1.0000
   4.750   0.6890   0.01745   0.00749  -0.0382   0.2388   1.0000
   5.000   0.7043   0.01821   0.00801  -0.0361   0.1966   1.0000
   5.250   0.7212   0.01889   0.00852  -0.0342   0.1688   1.0000
   5.500   0.7386   0.01955   0.00906  -0.0324   0.1500   1.0000
   5.750   0.7566   0.02018   0.00963  -0.0307   0.1361   1.0000
   6.000   0.7748   0.02083   0.01025  -0.0290   0.1255   1.0000
   6.250   0.7924   0.02155   0.01088  -0.0273   0.1166   1.0000
   6.500   0.8118   0.02218   0.01156  -0.0259   0.1084   1.0000
   6.750   0.8299   0.02296   0.01229  -0.0243   0.1016   1.0000
   7.000   0.8496   0.02365   0.01304  -0.0230   0.0948   1.0000
   7.250   0.8681   0.02451   0.01385  -0.0216   0.0892   1.0000
   7.500   0.8885   0.02528   0.01471  -0.0204   0.0834   1.0000
   7.750   0.9071   0.02618   0.01556  -0.0192   0.0786   1.0000
   8.000   0.9281   0.02705   0.01658  -0.0181   0.0735   1.0000
   8.250   0.9471   0.02791   0.01745  -0.0169   0.0692   1.0000
   8.500   0.9673   0.02897   0.01860  -0.0159   0.0652   1.0000
   8.750   0.9866   0.02992   0.01966  -0.0147   0.0612   1.0000
   9.000   1.0047   0.03094   0.02061  -0.0136   0.0583   1.0000
   9.250   1.0246   0.03218   0.02213  -0.0124   0.0548   1.0000
   9.500   1.0417   0.03319   0.02324  -0.0111   0.0520   1.0000
   9.750   1.0588   0.03439   0.02444  -0.0099   0.0499   1.0000
  10.000   1.0762   0.03606   0.02644  -0.0085   0.0475   1.0000
  10.250   1.0910   0.03741   0.02794  -0.0070   0.0454   1.0000
  10.500   1.1046   0.03851   0.02908  -0.0054   0.0439   1.0000
  10.750   1.1158   0.04031   0.03113  -0.0035   0.0423   1.0000
  11.000   1.1237   0.04239   0.03355  -0.0011   0.0408   1.0000
  11.250   1.1298   0.04440   0.03580   0.0013   0.0397   1.0000
  11.500   1.1343   0.04632   0.03793   0.0037   0.0388   1.0000
  11.750   1.1383   0.04810   0.03984   0.0060   0.0381   1.0000
  12.000   1.1425   0.04985   0.04167   0.0080   0.0375   1.0000
  12.250   1.1342   0.05284   0.04500   0.0109   0.0369   1.0000
  12.500   1.1186   0.05647   0.04904   0.0137   0.0363   1.0000
  12.750   1.1002   0.06045   0.05336   0.0158   0.0359   1.0000
  13.000   1.0788   0.06497   0.05819   0.0169   0.0356   1.0000
  13.250   1.0536   0.07034   0.06386   0.0168   0.0355   1.0000
  13.500   1.0233   0.07708   0.07088   0.0149   0.0355   1.0000
  13.750   0.9864   0.08603   0.08008   0.0104   0.0358   1.0000
  14.000   0.9423   0.09853   0.09279   0.0023   0.0365   1.0000
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