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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 50,000
Max Cl/Cd: 40.89 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-50000-n5.txt
Download as CSV file: xf-kc135winglet-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 Winglet (supercritical Whitcomb)         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4416   0.09882   0.09199  -0.0286   1.0000   0.1296
  -8.000  -0.4397   0.09618   0.08941  -0.0277   1.0000   0.1367
  -7.750  -0.4641   0.09428   0.08772  -0.0355   1.0000   0.1410
  -7.500  -0.4431   0.09060   0.08405  -0.0274   1.0000   0.1497
  -7.000  -0.4578   0.08458   0.07826  -0.0363   1.0000   0.1704
  -6.000  -0.3996   0.06256   0.05552  -0.0548   1.0000   0.0819
  -5.750  -0.3826   0.05776   0.05068  -0.0549   1.0000   0.0635
  -5.500  -0.3543   0.05279   0.04517  -0.0593   1.0000   0.0522
  -5.250  -0.3328   0.04893   0.04113  -0.0612   1.0000   0.0493
  -5.000  -0.3045   0.04494   0.03670  -0.0641   1.0000   0.0459
  -4.750  -0.2669   0.04171   0.03253  -0.0672   1.0000   0.0417
  -4.500  -0.2394   0.03888   0.02939  -0.0685   1.0000   0.0406
  -4.250  -0.2101   0.03611   0.02629  -0.0701   1.0000   0.0399
  -4.000  -0.1799   0.03374   0.02356  -0.0713   1.0000   0.0393
  -3.750  -0.1500   0.03173   0.02120  -0.0721   1.0000   0.0388
  -3.500  -0.1206   0.03001   0.01913  -0.0726   1.0000   0.0386
  -3.250  -0.0925   0.02856   0.01742  -0.0726   1.0000   0.0386
  -3.000  -0.0658   0.02736   0.01601  -0.0722   1.0000   0.0388
  -2.750  -0.0408   0.02644   0.01492  -0.0713   1.0000   0.0400
  -2.500  -0.0154   0.02561   0.01396  -0.0706   1.0000   0.0419
  -2.250   0.0128   0.02472   0.01298  -0.0710   1.0000   0.0451
  -2.000   0.0434   0.02409   0.01220  -0.0719   1.0000   0.0486
  -1.750   0.0754   0.02358   0.01149  -0.0731   1.0000   0.0525
  -1.500   0.1099   0.02302   0.01082  -0.0750   1.0000   0.0612
  -1.250   0.1445   0.02057   0.01131  -0.0760   1.0000   0.7451
  -1.000   0.1310   0.02044   0.01146  -0.0651   1.0000   0.8706
  -0.750   0.1120   0.01963   0.01086  -0.0552   1.0000   0.9882
  -0.500   0.1424   0.01994   0.01076  -0.0567   1.0000   1.0000
  -0.250   0.1740   0.02032   0.01084  -0.0586   1.0000   1.0000
   0.000   0.2105   0.02074   0.01100  -0.0613   0.9968   1.0000
   0.250   0.2501   0.02117   0.01123  -0.0647   0.9913   1.0000
   0.500   0.2912   0.02165   0.01156  -0.0682   0.9864   1.0000
   0.750   0.3282   0.02208   0.01188  -0.0710   0.9797   1.0000
   1.000   0.3689   0.02256   0.01228  -0.0745   0.9739   1.0000
   1.250   0.4061   0.02299   0.01268  -0.0772   0.9656   1.0000
   1.500   0.4454   0.02341   0.01311  -0.0802   0.9571   1.0000
   1.750   0.4872   0.02380   0.01355  -0.0836   0.9483   1.0000
   2.000   0.5246   0.02413   0.01394  -0.0859   0.9367   1.0000
   2.250   0.5676   0.02425   0.01418  -0.0889   0.9219   1.0000
   2.500   0.6155   0.02408   0.01419  -0.0922   0.9046   1.0000
   2.750   0.6567   0.02368   0.01396  -0.0938   0.8804   1.0000
   3.000   0.7020   0.02283   0.01330  -0.0951   0.8520   1.0000
   3.250   0.7424   0.02182   0.01252  -0.0950   0.8178   1.0000
   3.500   0.7735   0.02117   0.01203  -0.0936   0.7771   1.0000
   3.750   0.8005   0.02081   0.01181  -0.0919   0.7248   1.0000
   4.000   0.8305   0.02041   0.01143  -0.0902   0.6317   1.0000
   4.250   0.8590   0.02101   0.01080  -0.0878   0.4285   1.0000
   4.500   0.8724   0.02292   0.01179  -0.0856   0.3015   1.0000
   4.750   0.8902   0.02457   0.01296  -0.0844   0.2371   1.0000
   5.000   0.9114   0.02596   0.01412  -0.0837   0.1992   1.0000
   5.250   0.9342   0.02728   0.01536  -0.0832   0.1763   1.0000
   5.500   0.9595   0.02856   0.01666  -0.0829   0.1607   1.0000
   5.750   0.9864   0.02983   0.01798  -0.0828   0.1465   1.0000
   6.000   1.0134   0.03115   0.01936  -0.0828   0.1338   1.0000
   6.250   1.0430   0.03262   0.02098  -0.0829   0.1247   1.0000
   6.500   1.0726   0.03434   0.02290  -0.0831   0.1160   1.0000
   6.750   1.0977   0.03596   0.02461  -0.0829   0.1062   1.0000
   7.000   1.1215   0.03758   0.02644  -0.0825   0.0966   1.0000
   7.250   1.1449   0.03960   0.02881  -0.0820   0.0881   1.0000
   7.500   1.1671   0.04154   0.03080  -0.0816   0.0816   1.0000
   7.750   1.1867   0.04403   0.03390  -0.0805   0.0747   1.0000
   8.000   1.2058   0.04640   0.03653  -0.0796   0.0701   1.0000
   8.250   1.2241   0.04940   0.03970  -0.0788   0.0674   1.0000
   8.500   1.2349   0.05341   0.04448  -0.0768   0.0653   1.0000
   8.750   1.2410   0.05763   0.04932  -0.0746   0.0636   1.0000
   9.000   1.2424   0.06197   0.05421  -0.0723   0.0624   1.0000
   9.250   1.2392   0.06635   0.05906  -0.0699   0.0614   1.0000
   9.500   1.2320   0.07063   0.06373  -0.0675   0.0604   1.0000
   9.750   1.2216   0.07472   0.06814  -0.0652   0.0594   1.0000
  10.000   1.2053   0.07880   0.07247  -0.0627   0.0588   1.0000
  10.250   1.1814   0.08357   0.07748  -0.0608   0.0588   1.0000
  10.500   1.1479   0.09018   0.08433  -0.0610   0.0596   1.0000
  10.750   1.1119   0.09870   0.09300  -0.0645   0.0610   1.0000
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