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LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL610.61 AIRFOIL (c141d-il)
Reynolds number: 200,000
Max Cl/Cd: 67.04 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141d-il-200000.txt
Download as CSV file: xf-c141d-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3732   0.10943   0.10571  -0.0363   1.0000   0.0609
 -10.750  -0.3964   0.10423   0.10055  -0.0401   1.0000   0.0630
 -10.500  -0.4217   0.09848   0.09486  -0.0442   1.0000   0.0634
 -10.250  -0.4228   0.09385   0.09026  -0.0434   1.0000   0.0640
 -10.000  -0.4093   0.09202   0.08843  -0.0402   1.0000   0.0648
  -9.750  -0.4067   0.08938   0.08582  -0.0389   1.0000   0.0657
  -9.500  -0.4092   0.08625   0.08271  -0.0382   1.0000   0.0668
  -9.250  -0.4164   0.08263   0.07913  -0.0380   1.0000   0.0680
  -9.000  -0.4283   0.07856   0.07510  -0.0382   1.0000   0.0691
  -8.750  -0.6286   0.07511   0.07132  -0.0432   1.0000   0.0641
  -8.500  -0.6104   0.07347   0.06980  -0.0409   1.0000   0.0650
  -8.250  -0.6149   0.07127   0.06761  -0.0383   1.0000   0.0657
  -8.000  -0.6232   0.06870   0.06502  -0.0359   1.0000   0.0665
  -7.750  -0.6316   0.06589   0.06216  -0.0335   1.0000   0.0674
  -7.500  -0.6392   0.06285   0.05903  -0.0312   1.0000   0.0688
  -7.250  -0.7130   0.03957   0.03365  -0.0236   1.0000   0.0407
  -7.000  -0.7033   0.03622   0.03010  -0.0216   1.0000   0.0403
  -6.750  -0.6923   0.03296   0.02646  -0.0195   1.0000   0.0401
  -6.500  -0.6783   0.03000   0.02299  -0.0176   1.0000   0.0403
  -6.250  -0.6610   0.02751   0.02009  -0.0161   1.0000   0.0412
  -6.000  -0.6410   0.02680   0.01947  -0.0153   1.0000   0.0429
  -5.750  -0.6204   0.02564   0.01812  -0.0143   1.0000   0.0448
  -5.500  -0.5984   0.02402   0.01610  -0.0131   1.0000   0.0466
  -5.250  -0.5759   0.02253   0.01443  -0.0123   1.0000   0.0486
  -5.000  -0.5540   0.02185   0.01373  -0.0115   1.0000   0.0512
  -4.750  -0.5232   0.02098   0.01268  -0.0122   0.9984   0.0559
  -4.500  -0.4878   0.02055   0.01225  -0.0141   0.9957   0.0615
  -4.250  -0.4531   0.01985   0.01154  -0.0158   0.9932   0.0675
  -4.000  -0.4196   0.01941   0.01100  -0.0171   0.9898   0.0747
  -3.750  -0.3846   0.01901   0.01065  -0.0190   0.9867   0.0826
  -3.500  -0.3483   0.01840   0.01009  -0.0210   0.9844   0.0907
  -3.250  -0.3170   0.01811   0.00973  -0.0219   0.9800   0.0985
  -3.000  -0.2837   0.01746   0.00922  -0.0234   0.9765   0.1089
  -2.750  -0.2472   0.01704   0.00888  -0.0255   0.9736   0.1222
  -2.500  -0.2141   0.01668   0.00859  -0.0268   0.9698   0.1412
  -2.250  -0.1834   0.01615   0.00829  -0.0278   0.9650   0.1767
  -2.000  -0.1544   0.01419   0.00811  -0.0293   0.9628   0.5466
  -1.750  -0.1257   0.01363   0.00843  -0.0286   0.9601   0.7729
  -1.500  -0.1029   0.01366   0.00869  -0.0266   0.9546   0.8562
  -1.250  -0.0721   0.01387   0.00895  -0.0262   0.9499   0.9158
  -1.000  -0.0260   0.01418   0.00921  -0.0293   0.9479   0.9572
  -0.750   0.0330   0.01446   0.00941  -0.0355   0.9474   0.9773
  -0.500   0.1116   0.01480   0.00967  -0.0460   0.9499   0.9952
  -0.250   0.1651   0.01481   0.00963  -0.0516   0.9480   1.0000
   0.000   0.2082   0.01475   0.00953  -0.0551   0.9451   1.0000
   0.250   0.2288   0.01468   0.00943  -0.0542   0.9352   1.0000
   0.500   0.2717   0.01458   0.00932  -0.0575   0.9318   1.0000
   0.750   0.2966   0.01454   0.00926  -0.0572   0.9231   1.0000
   1.000   0.3545   0.01410   0.00883  -0.0629   0.9182   1.0000
   1.250   0.4162   0.01314   0.00789  -0.0684   0.9078   1.0000
   1.500   0.4682   0.01212   0.00689  -0.0719   0.8972   1.0000
   1.750   0.4983   0.01157   0.00634  -0.0715   0.8838   1.0000
   2.000   0.5223   0.01124   0.00604  -0.0702   0.8700   1.0000
   2.250   0.5472   0.01095   0.00576  -0.0691   0.8558   1.0000
   2.500   0.5725   0.01068   0.00549  -0.0680   0.8397   1.0000
   2.750   0.5980   0.01044   0.00526  -0.0670   0.8209   1.0000
   3.000   0.6211   0.01029   0.00509  -0.0655   0.7970   1.0000
   3.250   0.6446   0.01016   0.00492  -0.0640   0.7673   1.0000
   3.500   0.6672   0.01012   0.00477  -0.0624   0.7257   1.0000
   3.750   0.6878   0.01026   0.00466  -0.0603   0.6627   1.0000
   4.000   0.7013   0.01076   0.00467  -0.0569   0.5622   1.0000
   4.250   0.7032   0.01182   0.00495  -0.0516   0.4161   1.0000
   4.500   0.7037   0.01312   0.00547  -0.0467   0.2814   1.0000
   4.750   0.7116   0.01417   0.00601  -0.0431   0.2045   1.0000
   5.000   0.7249   0.01492   0.00653  -0.0404   0.1700   1.0000
   5.250   0.7405   0.01555   0.00701  -0.0381   0.1510   1.0000
   5.500   0.7575   0.01612   0.00751  -0.0361   0.1378   1.0000
   5.750   0.7747   0.01676   0.00808  -0.0342   0.1276   1.0000
   6.000   0.7928   0.01739   0.00863  -0.0324   0.1186   1.0000
   6.250   0.8124   0.01799   0.00924  -0.0309   0.1109   1.0000
   6.500   0.8310   0.01886   0.00999  -0.0294   0.1035   1.0000
   6.750   0.8522   0.01937   0.01060  -0.0282   0.0970   1.0000
   7.000   0.8726   0.02041   0.01150  -0.0271   0.0903   1.0000
   7.250   0.8940   0.02091   0.01212  -0.0259   0.0847   1.0000
   7.500   0.9152   0.02181   0.01293  -0.0250   0.0791   1.0000
   7.750   0.9370   0.02256   0.01381  -0.0239   0.0740   1.0000
   8.000   0.9579   0.02327   0.01447  -0.0230   0.0694   1.0000
   8.250   0.9806   0.02441   0.01569  -0.0222   0.0652   1.0000
   8.500   1.0012   0.02511   0.01646  -0.0211   0.0612   1.0000
   8.750   1.0240   0.02642   0.01771  -0.0206   0.0578   1.0000
   9.000   1.0442   0.02734   0.01885  -0.0193   0.0548   1.0000
   9.250   1.0648   0.02831   0.01988  -0.0183   0.0523   1.0000
   9.500   1.0881   0.03004   0.02158  -0.0181   0.0500   1.0000
   9.750   1.1047   0.03126   0.02312  -0.0162   0.0479   1.0000
  10.000   1.1225   0.03240   0.02440  -0.0149   0.0459   1.0000
  10.250   1.1407   0.03357   0.02562  -0.0137   0.0444   1.0000
  10.500   1.1598   0.03600   0.02813  -0.0131   0.0432   1.0000
  10.750   1.1676   0.03814   0.03072  -0.0102   0.0424   1.0000
  11.000   1.1727   0.04077   0.03375  -0.0073   0.0417   1.0000
  11.250   1.1740   0.04357   0.03694  -0.0041   0.0410   1.0000
  11.500   1.1709   0.04632   0.04003  -0.0005   0.0405   1.0000
  11.750   1.1632   0.04896   0.04294   0.0035   0.0400   1.0000
  12.000   1.1532   0.05165   0.04589   0.0073   0.0396   1.0000
  12.250   1.1417   0.05445   0.04891   0.0106   0.0393   1.0000
  12.500   1.1220   0.05810   0.05284   0.0138   0.0392   1.0000
  12.750   1.0835   0.06394   0.05906   0.0165   0.0396   1.0000
  13.000   1.0380   0.07139   0.06686   0.0167   0.0403   1.0000
  13.250   0.9948   0.07989   0.07562   0.0140   0.0411   1.0000
  13.500   0.9553   0.08965   0.08557   0.0085   0.0419   1.0000
  13.750   0.9222   0.10034   0.09637   0.0016   0.0426   1.0000
  14.000   0.9016   0.10951   0.10557  -0.0036   0.0432   1.0000
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