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KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il)
Reynolds number: 50,000
Max Cl/Cd: 31.77 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kc135b-il-50000-n5.txt
Download as CSV file: xf-kc135b-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 BL124.32 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.4974   0.13276   0.12535  -0.0219   1.0000   0.1344
 -11.750  -0.4785   0.12817   0.12076  -0.0205   1.0000   0.1390
 -11.500  -0.4791   0.12512   0.11775  -0.0218   1.0000   0.1483
 -11.250  -0.4770   0.12123   0.11392  -0.0226   1.0000   0.1541
 -11.000  -0.4697   0.11790   0.11060  -0.0228   1.0000   0.1611
 -10.500  -0.3945   0.09284   0.08603  -0.0399   1.0000   0.0708
 -10.250  -0.3979   0.08788   0.08109  -0.0414   1.0000   0.0683
 -10.000  -0.4117   0.08158   0.07482  -0.0446   1.0000   0.0657
  -9.750  -0.4403   0.07470   0.06792  -0.0486   1.0000   0.0634
  -9.500  -0.4886   0.06908   0.06219  -0.0510   1.0000   0.0615
  -9.000  -0.5961   0.07275   0.06520  -0.0441   1.0000   0.0595
  -8.750  -0.5971   0.06930   0.06172  -0.0427   1.0000   0.0587
  -8.500  -0.6009   0.06618   0.05850  -0.0408   1.0000   0.0579
  -8.250  -0.6052   0.06322   0.05542  -0.0384   1.0000   0.0572
  -8.000  -0.6091   0.06042   0.05248  -0.0357   1.0000   0.0566
  -7.750  -0.6118   0.05782   0.04971  -0.0328   1.0000   0.0560
  -7.500  -0.6142   0.05534   0.04704  -0.0297   1.0000   0.0555
  -7.250  -0.6162   0.05309   0.04458  -0.0262   1.0000   0.0550
  -7.000  -0.6177   0.05103   0.04231  -0.0227   1.0000   0.0548
  -6.750  -0.6181   0.04915   0.04019  -0.0192   1.0000   0.0550
  -6.500  -0.6169   0.04738   0.03816  -0.0158   1.0000   0.0557
  -6.250  -0.6120   0.04561   0.03609  -0.0129   0.9994   0.0566
  -6.000  -0.5829   0.04302   0.03297  -0.0143   0.9905   0.0576
  -5.750  -0.5521   0.04054   0.03005  -0.0155   0.9823   0.0580
  -5.500  -0.5188   0.03829   0.02739  -0.0169   0.9750   0.0584
  -5.250  -0.4871   0.03650   0.02518  -0.0177   0.9668   0.0596
  -5.000  -0.4530   0.03445   0.02297  -0.0193   0.9602   0.0625
  -4.750  -0.4176   0.03287   0.02132  -0.0209   0.9534   0.0653
  -4.500  -0.3757   0.03143   0.01976  -0.0230   0.9490   0.0677
  -4.250  -0.3424   0.03047   0.01862  -0.0236   0.9412   0.0721
  -4.000  -0.3054   0.02929   0.01743  -0.0251   0.9358   0.0769
  -3.750  -0.2772   0.02840   0.01647  -0.0254   0.9280   0.0813
  -3.500  -0.2474   0.02761   0.01550  -0.0261   0.9208   0.0890
  -3.250  -0.2231   0.02669   0.01454  -0.0262   0.9126   0.0967
  -3.000  -0.1960   0.02585   0.01361  -0.0267   0.9051   0.1091
  -2.750  -0.1713   0.02496   0.01274  -0.0268   0.8975   0.1308
  -2.500  -0.1689   0.02243   0.01247  -0.0231   0.8891   0.5289
  -2.250  -0.1555   0.02266   0.01302  -0.0184   0.8809   0.6843
  -2.000  -0.1345   0.02311   0.01355  -0.0149   0.8741   0.7566
  -1.750  -0.0967   0.02399   0.01444  -0.0130   0.8705   0.8214
  -1.500  -0.0482   0.02484   0.01513  -0.0144   0.8658   0.8579
  -1.250  -0.0181   0.02479   0.01488  -0.0153   0.8587   0.8667
  -1.000   0.0238   0.02471   0.01461  -0.0183   0.8542   0.8731
  -0.750   0.0479   0.02478   0.01458  -0.0183   0.8453   0.8826
  -0.500   0.0885   0.02476   0.01442  -0.0211   0.8402   0.8894
  -0.250   0.1187   0.02484   0.01441  -0.0222   0.8330   0.8990
   0.000   0.1575   0.02490   0.01439  -0.0249   0.8267   0.9062
   0.250   0.1984   0.02488   0.01428  -0.0277   0.8222   0.9145
   0.500   0.2318   0.02509   0.01447  -0.0297   0.8141   0.9233
   0.750   0.2690   0.02512   0.01447  -0.0320   0.8084   0.9330
   1.000   0.3097   0.02526   0.01461  -0.0353   0.8019   0.9410
   1.250   0.3461   0.02539   0.01475  -0.0376   0.7949   0.9513
   1.500   0.3896   0.02536   0.01473  -0.0410   0.7901   0.9600
   1.750   0.4225   0.02565   0.01509  -0.0432   0.7810   0.9721
   2.000   0.4670   0.02553   0.01502  -0.0466   0.7747   0.9810
   2.250   0.5036   0.02558   0.01514  -0.0491   0.7629   0.9929
   2.500   0.5345   0.02550   0.01511  -0.0501   0.7511   1.0000
   2.750   0.5526   0.02538   0.01502  -0.0483   0.7409   1.0000
   3.000   0.5609   0.02559   0.01525  -0.0453   0.7289   1.0000
   3.250   0.5696   0.02585   0.01554  -0.0422   0.7170   1.0000
   3.500   0.5856   0.02589   0.01560  -0.0400   0.7051   1.0000
   3.750   0.6070   0.02572   0.01548  -0.0383   0.6929   1.0000
   4.000   0.6247   0.02566   0.01547  -0.0360   0.6790   1.0000
   4.250   0.6401   0.02570   0.01556  -0.0335   0.6642   1.0000
   4.500   0.6566   0.02573   0.01565  -0.0312   0.6493   1.0000
   4.750   0.6740   0.02574   0.01575  -0.0290   0.6342   1.0000
   5.000   0.6923   0.02570   0.01580  -0.0268   0.6185   1.0000
   5.250   0.7115   0.02561   0.01580  -0.0247   0.6019   1.0000
   5.500   0.7281   0.02563   0.01591  -0.0223   0.5834   1.0000
   5.750   0.7426   0.02571   0.01612  -0.0196   0.5621   1.0000
   6.000   0.7627   0.02554   0.01603  -0.0175   0.5401   1.0000
   6.250   0.7771   0.02565   0.01623  -0.0149   0.5131   1.0000
   6.500   0.7940   0.02569   0.01631  -0.0125   0.4832   1.0000
   6.750   0.8116   0.02576   0.01637  -0.0101   0.4498   1.0000
   7.000   0.8270   0.02603   0.01654  -0.0076   0.4140   1.0000
   7.250   0.8410   0.02652   0.01687  -0.0051   0.3794   1.0000
   7.500   0.8535   0.02723   0.01739  -0.0026   0.3486   1.0000
   7.750   0.8648   0.02813   0.01813  -0.0001   0.3218   1.0000
   8.000   0.8754   0.02914   0.01900   0.0022   0.2974   1.0000
   8.250   0.8838   0.03021   0.02004   0.0047   0.2729   1.0000
   8.500   0.8891   0.03131   0.02103   0.0074   0.2502   1.0000
   8.750   0.8918   0.03244   0.02216   0.0104   0.2273   1.0000
   9.000   0.8946   0.03368   0.02334   0.0130   0.2071   1.0000
   9.250   0.8981   0.03504   0.02468   0.0153   0.1870   1.0000
   9.500   0.9016   0.03654   0.02618   0.0173   0.1672   1.0000
   9.750   0.9051   0.03819   0.02779   0.0191   0.1491   1.0000
  10.000   0.9083   0.03997   0.02952   0.0208   0.1326   1.0000
  10.250   0.9129   0.04184   0.03137   0.0222   0.1174   1.0000
  10.500   0.9176   0.04376   0.03328   0.0234   0.1054   1.0000
  10.750   0.9253   0.04569   0.03530   0.0246   0.0952   1.0000
  11.000   0.9336   0.04767   0.03737   0.0256   0.0869   1.0000
  11.250   0.9406   0.04964   0.03928   0.0265   0.0811   1.0000
  11.500   0.9535   0.05175   0.04165   0.0275   0.0753   1.0000
  11.750   0.9622   0.05383   0.04380   0.0283   0.0710   1.0000
  12.000   0.9703   0.05623   0.04635   0.0290   0.0672   1.0000
  12.250   0.9749   0.05902   0.04944   0.0296   0.0640   1.0000
  12.500   0.9789   0.06183   0.05245   0.0301   0.0617   1.0000
  12.750   0.9835   0.06451   0.05520   0.0305   0.0596   1.0000
  13.000   0.9828   0.06787   0.05870   0.0306   0.0578   1.0000
  13.250   0.9714   0.07236   0.06353   0.0300   0.0568   1.0000
  13.500   0.9564   0.07740   0.06886   0.0288   0.0560   1.0000
  13.750   0.9385   0.08315   0.07487   0.0269   0.0557   1.0000
  14.000   0.9155   0.08998   0.08194   0.0239   0.0555   1.0000
  14.250   0.8883   0.09825   0.09041   0.0196   0.0558   1.0000
  14.500   0.8588   0.10805   0.10038   0.0141   0.0566   1.0000
  14.750   0.8289   0.11928   0.11169   0.0077   0.0574   1.0000
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