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BOEING 707 .40 SPAN AIRFOIL (b707c-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: BOEING 707 .40 SPAN AIRFOIL (b707c-il)
Reynolds number: 100,000
Max Cl/Cd: 42.39 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-b707c-il-100000.txt
Download as CSV file: xf-b707c-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BOEING 707 .40 SPAN 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5035   0.09309   0.08798  -0.0348   1.0000   0.0666
  -8.750  -0.5208   0.09038   0.08526  -0.0360   1.0000   0.0668
  -8.500  -0.5358   0.08816   0.08294  -0.0366   1.0000   0.0670
  -8.250  -0.5004   0.08181   0.07683  -0.0333   1.0000   0.0702
  -8.000  -0.5021   0.07861   0.07365  -0.0332   1.0000   0.0720
  -7.750  -0.5063   0.07541   0.07044  -0.0334   1.0000   0.0739
  -7.500  -0.5125   0.07244   0.06740  -0.0336   1.0000   0.0764
  -7.250  -0.5289   0.07211   0.06664  -0.0331   1.0000   0.0788
  -7.000  -0.5210   0.06658   0.06126  -0.0324   1.0000   0.0803
  -6.750  -0.5113   0.06294   0.05774  -0.0310   1.0000   0.0833
  -6.500  -0.5067   0.06046   0.05516  -0.0297   1.0000   0.0879
  -6.250  -0.5084   0.05931   0.05354  -0.0279   1.0000   0.0927
  -6.000  -0.4976   0.05474   0.04921  -0.0268   1.0000   0.0959
  -5.750  -0.4935   0.05641   0.05020  -0.0239   1.0000   0.1055
  -5.500  -0.4832   0.04982   0.04397  -0.0235   1.0000   0.1085
  -5.250  -0.4754   0.05062   0.04422  -0.0208   1.0000   0.1198
  -5.000  -0.4643   0.04472   0.03869  -0.0202   1.0000   0.1243
  -4.750  -0.4551   0.04255   0.03633  -0.0184   1.0000   0.1369
  -4.500  -0.4453   0.04011   0.03381  -0.0168   1.0000   0.1520
  -4.250  -0.4355   0.03753   0.03125  -0.0152   1.0000   0.1709
  -4.000  -0.4272   0.03520   0.02888  -0.0135   1.0000   0.1989
  -3.750  -0.4177   0.03316   0.02677  -0.0117   1.0000   0.2268
  -3.500  -0.4076   0.03115   0.02470  -0.0099   1.0000   0.2554
  -3.250  -0.3959   0.02887   0.02258  -0.0082   1.0000   0.2776
  -3.000  -0.3720   0.02700   0.02069  -0.0085   0.9967   0.3036
  -2.750  -0.3203   0.02499   0.01825  -0.0130   0.9870   0.3106
  -2.500  -0.2469   0.02542   0.01742  -0.0175   0.9758   0.2076
  -2.250  -0.1831   0.02534   0.01662  -0.0195   0.9654   0.1162
  -2.000  -0.1294   0.02389   0.01480  -0.0225   0.9580   0.0890
  -1.750  -0.0854   0.02272   0.01335  -0.0243   0.9463   0.0787
  -1.500  -0.0424   0.02115   0.01185  -0.0269   0.9367   0.0775
  -1.250   0.0032   0.01995   0.01069  -0.0297   0.9284   0.0786
  -1.000   0.0403   0.01884   0.00970  -0.0311   0.9172   0.0790
  -0.750   0.0831   0.01769   0.00864  -0.0338   0.9103   0.0844
  -0.500   0.1166   0.01708   0.00800  -0.0346   0.8971   0.0979
  -0.250   0.1507   0.01635   0.00728  -0.0353   0.8847   0.1343
   0.000   0.3164   0.01331   0.00680  -0.0558   0.8749   1.0000
   0.250   0.3459   0.01296   0.00625  -0.0554   0.8375   1.0000
   0.500   0.3723   0.01282   0.00595  -0.0550   0.8139   1.0000
   0.750   0.3946   0.01276   0.00579  -0.0539   0.7908   1.0000
   1.000   0.4167   0.01270   0.00557  -0.0525   0.7651   1.0000
   1.250   0.4360   0.01270   0.00546  -0.0507   0.7393   1.0000
   1.500   0.4565   0.01275   0.00542  -0.0492   0.7197   1.0000
   1.750   0.4768   0.01283   0.00542  -0.0477   0.7016   1.0000
   2.000   0.4952   0.01294   0.00541  -0.0456   0.6755   1.0000
   2.250   0.5149   0.01307   0.00546  -0.0439   0.6551   1.0000
   2.500   0.5334   0.01322   0.00551  -0.0419   0.6273   1.0000
   2.750   0.5510   0.01338   0.00556  -0.0396   0.5940   1.0000
   3.000   0.5678   0.01353   0.00561  -0.0372   0.5515   1.0000
   3.250   0.5829   0.01375   0.00557  -0.0345   0.4731   1.0000
   3.500   0.5891   0.01495   0.00565  -0.0306   0.2671   1.0000
   3.750   0.6011   0.01621   0.00633  -0.0282   0.1922   1.0000
   4.000   0.6163   0.01714   0.00679  -0.0262   0.1148   1.0000
   4.250   0.6336   0.01785   0.00744  -0.0244   0.1032   1.0000
   4.500   0.6522   0.01844   0.00806  -0.0228   0.0970   1.0000
   4.750   0.6695   0.01917   0.00878  -0.0210   0.0929   1.0000
   5.000   0.6891   0.01971   0.00940  -0.0195   0.0906   1.0000
   5.250   0.7081   0.02031   0.01011  -0.0180   0.0885   1.0000
   5.500   0.7267   0.02101   0.01083  -0.0164   0.0847   1.0000
   5.750   0.7441   0.02191   0.01170  -0.0148   0.0811   1.0000
   6.000   0.7628   0.02301   0.01276  -0.0132   0.0789   1.0000
   6.250   0.7843   0.02392   0.01377  -0.0120   0.0748   1.0000
   6.500   0.8052   0.02528   0.01507  -0.0111   0.0688   1.0000
   6.750   0.8307   0.02717   0.01702  -0.0104   0.0633   1.0000
   7.000   0.8553   0.02892   0.01879  -0.0098   0.0590   1.0000
   7.250   0.8824   0.03188   0.02173  -0.0099   0.0559   1.0000
   7.500   0.9051   0.03396   0.02416  -0.0088   0.0550   1.0000
   7.750   0.9263   0.03655   0.02707  -0.0076   0.0550   1.0000
   8.000   0.9456   0.03954   0.03035  -0.0064   0.0554   1.0000
   8.250   0.9644   0.04369   0.03472  -0.0055   0.0563   1.0000
   8.500   0.9716   0.04516   0.03715  -0.0013   0.0604   1.0000
   8.750   0.9795   0.04951   0.04194   0.0010   0.0646   1.0000
   9.000   0.9763   0.05452   0.04771   0.0047   0.0750   1.0000
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