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KC-135 BL351.6 AIRFOIL (kc135d-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: KC-135 BL351.6 AIRFOIL (kc135d-il)
Reynolds number: 1,000,000
Max Cl/Cd: 114.87 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135d-il-1000000.txt
Download as CSV file: xf-kc135d-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 BL351.6 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4770   0.06984   0.06827  -0.0391   1.0000   0.0079
  -7.750  -0.4798   0.06631   0.06471  -0.0394   1.0000   0.0079
  -7.500  -0.4830   0.06308   0.06145  -0.0386   1.0000   0.0079
  -7.250  -0.4668   0.05896   0.05725  -0.0421   0.9965   0.0080
  -7.000  -0.4473   0.05487   0.05307  -0.0456   0.9892   0.0082
  -6.750  -0.4238   0.05072   0.04880  -0.0494   0.9834   0.0084
  -6.500  -0.3992   0.04680   0.04475  -0.0525   0.9756   0.0088
  -6.250  -0.3710   0.04275   0.04052  -0.0556   0.9681   0.0094
  -6.000  -0.3358   0.03898   0.03647  -0.0569   0.9572   0.0110
  -5.500  -0.2933   0.01767   0.01477  -0.0507   0.8874   0.0111
  -5.250  -0.2869   0.01269   0.00945  -0.0493   0.8760   0.0117
  -5.000  -0.2682   0.01114   0.00775  -0.0486   0.8664   0.0120
  -4.750  -0.2479   0.00995   0.00642  -0.0480   0.8572   0.0126
  -4.500  -0.2258   0.00870   0.00499  -0.0472   0.8484   0.0139
  -4.250  -0.2040   0.01551   0.01073  -0.0473   0.8627   0.0114
  -4.000  -0.1804   0.01432   0.00937  -0.0466   0.8538   0.0121
  -3.750  -0.1549   0.01415   0.00914  -0.0464   0.8450   0.0129
  -3.500  -0.1293   0.01292   0.00773  -0.0457   0.8371   0.0137
  -3.250  -0.1036   0.01174   0.00637  -0.0450   0.8294   0.0144
  -3.000  -0.0769   0.01140   0.00595  -0.0446   0.8215   0.0154
  -2.750  -0.0530   0.01003   0.00443  -0.0438   0.8143   0.0169
  -2.500  -0.0275   0.00955   0.00394  -0.0434   0.8067   0.0178
  -2.250  -0.0019   0.00922   0.00355  -0.0429   0.7998   0.0189
  -2.000   0.0240   0.00888   0.00319  -0.0425   0.7920   0.0202
  -1.750   0.0498   0.00863   0.00289  -0.0421   0.7843   0.0216
  -1.500   0.0761   0.00844   0.00265  -0.0417   0.7757   0.0224
  -1.250   0.1004   0.00797   0.00210  -0.0410   0.7667   0.0234
  -1.000   0.1251   0.00759   0.00163  -0.0404   0.7570   0.0257
  -0.750   0.1515   0.00744   0.00144  -0.0401   0.7465   0.0285
  -0.500   0.1781   0.00731   0.00127  -0.0398   0.7371   0.0308
  -0.250   0.2048   0.00724   0.00114  -0.0396   0.7287   0.0326
   0.000   0.2317   0.00710   0.00098  -0.0394   0.7211   0.0412
   0.250   0.2450   0.00535   0.00086  -0.0372   0.7137   0.6307
   0.500   0.2672   0.00500   0.00087  -0.0361   0.7054   0.7406
   0.750   0.2899   0.00478   0.00089  -0.0348   0.6976   0.8184
   1.000   0.3132   0.00463   0.00093  -0.0337   0.6888   0.8860
   1.250   0.3434   0.00458   0.00100  -0.0340   0.6802   0.9393
   1.500   0.3845   0.00465   0.00106  -0.0369   0.6710   0.9660
   1.750   0.4252   0.00474   0.00112  -0.0398   0.6600   0.9770
   2.000   0.4573   0.00481   0.00116  -0.0408   0.6490   0.9833
   2.250   0.4942   0.00489   0.00120  -0.0429   0.6356   0.9861
   2.500   0.5296   0.00497   0.00124  -0.0447   0.6209   0.9897
   2.750   0.5633   0.00509   0.00130  -0.0462   0.6024   0.9935
   3.000   0.5980   0.00521   0.00135  -0.0479   0.5767   0.9963
   3.250   0.6318   0.00550   0.00144  -0.0495   0.5182   0.9991
   3.500   0.6560   0.00595   0.00158  -0.0491   0.4433   1.0000
   3.750   0.6734   0.00652   0.00180  -0.0473   0.3601   1.0000
   4.000   0.6916   0.00706   0.00204  -0.0457   0.2949   1.0000
   4.250   0.7118   0.00746   0.00226  -0.0444   0.2505   1.0000
   4.500   0.7334   0.00775   0.00244  -0.0433   0.2240   1.0000
   4.750   0.7552   0.00804   0.00264  -0.0423   0.1999   1.0000
   5.000   0.7769   0.00836   0.00284  -0.0413   0.1731   1.0000
   5.250   0.7977   0.00875   0.00308  -0.0401   0.1397   1.0000
   5.500   0.8153   0.00942   0.00348  -0.0384   0.0829   1.0000
   5.750   0.8316   0.01025   0.00402  -0.0365   0.0322   1.0000
   6.000   0.8524   0.01071   0.00445  -0.0353   0.0228   1.0000
   6.250   0.8748   0.01102   0.00479  -0.0344   0.0202   1.0000
   6.500   0.8956   0.01150   0.00529  -0.0331   0.0164   1.0000
   6.750   0.9165   0.01197   0.00583  -0.0319   0.0146   1.0000
   7.000   0.9385   0.01235   0.00624  -0.0310   0.0133   1.0000
   7.250   0.9599   0.01278   0.00672  -0.0299   0.0123   1.0000
   7.500   0.9801   0.01334   0.00731  -0.0287   0.0113   1.0000
   7.750   0.9939   0.01452   0.00865  -0.0263   0.0103   1.0000
   8.000   1.0132   0.01515   0.00935  -0.0250   0.0100   1.0000
   8.250   1.0343   0.01561   0.00985  -0.0240   0.0094   1.0000
   8.500   1.0539   0.01619   0.01050  -0.0228   0.0090   1.0000
   8.750   1.0723   0.01688   0.01126  -0.0214   0.0085   1.0000
   9.000   1.0895   0.01768   0.01213  -0.0198   0.0082   1.0000
   9.250   1.1058   0.01858   0.01313  -0.0182   0.0080   1.0000
   9.500   1.1230   0.01932   0.01393  -0.0167   0.0077   1.0000
   9.750   1.1379   0.02029   0.01498  -0.0150   0.0075   1.0000
  10.000   1.1500   0.02159   0.01638  -0.0129   0.0072   1.0000
  10.250   1.1597   0.02332   0.01825  -0.0105   0.0071   1.0000
  10.500   1.1611   0.02680   0.02204  -0.0073   0.0067   1.0000
  10.750   1.1713   0.02744   0.02279  -0.0048   0.0066   1.0000
  11.000   1.1822   0.02779   0.02322  -0.0025   0.0063   1.0000
  11.250   1.1852   0.02964   0.02526   0.0005   0.0062   1.0000
  11.500   1.1932   0.03044   0.02617   0.0026   0.0059   1.0000
  11.750   1.1899   0.03296   0.02891   0.0056   0.0060   1.0000
  12.000   1.1898   0.03479   0.03091   0.0079   0.0058   1.0000
  12.250   1.1849   0.03725   0.03356   0.0102   0.0056   1.0000
  12.500   1.1744   0.04042   0.03696   0.0123   0.0056   1.0000
  12.750   1.1687   0.04305   0.03974   0.0135   0.0055   1.0000
  13.000   1.1480   0.04778   0.04473   0.0145   0.0055   1.0000
  13.250   1.1454   0.05036   0.04741   0.0145   0.0054   1.0000
  13.500   1.1261   0.05548   0.05273   0.0138   0.0054   1.0000
  13.750   1.0987   0.06234   0.05983   0.0118   0.0055   1.0000
  14.000   1.0684   0.07051   0.06821   0.0080   0.0056   1.0000
  14.250   1.0361   0.08033   0.07824   0.0023   0.0058   1.0000
  14.500   1.0417   0.08338   0.08132   0.0001   0.0054   1.0000
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