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KC-135 BL124.32 AIRFOIL (kc135b-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: KC-135 BL124.32 AIRFOIL (kc135b-il)
Reynolds number: 50,000
Max Cl/Cd: 31.06 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135b-il-50000.txt
Download as CSV file: xf-kc135b-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4564   0.12918   0.12189  -0.0103   1.0000   0.2878
 -11.000  -0.4545   0.12652   0.11928  -0.0101   1.0000   0.3038
 -10.750  -0.4564   0.12425   0.11707  -0.0099   1.0000   0.3199
 -10.500  -0.4193   0.11865   0.11142  -0.0084   1.0000   0.3428
 -10.250  -0.4218   0.11682   0.10964  -0.0077   1.0000   0.3643
 -10.000  -0.4006   0.11273   0.10555  -0.0068   1.0000   0.3872
  -9.750  -0.4084   0.11169   0.10458  -0.0055   1.0000   0.4110
  -9.500  -0.3822   0.10755   0.10043  -0.0045   1.0000   0.4392
  -9.250  -0.3654   0.10400   0.09690  -0.0038   1.0000   0.4629
  -9.000  -0.3671   0.10254   0.09550  -0.0023   1.0000   0.4867
  -8.500  -0.3504   0.09644   0.08949  -0.0012   1.0000   0.5191
  -8.250  -0.3320   0.09196   0.08502  -0.0022   1.0000   0.5236
  -8.000  -0.3367   0.08984   0.08296  -0.0013   1.0000   0.5321
  -7.750  -0.3368   0.08604   0.07923  -0.0023   1.0000   0.5212
  -7.500  -0.4428   0.07689   0.07052  -0.0138   1.0000   0.3695
  -7.250  -0.5107   0.06993   0.06392  -0.0178   1.0000   0.3265
  -6.750  -0.6152   0.05961   0.05364  -0.0172   1.0000   0.2780
  -6.500  -0.6409   0.05551   0.04916  -0.0154   1.0000   0.2487
  -6.250  -0.6510   0.05185   0.04492  -0.0134   1.0000   0.2178
  -6.000  -0.6479   0.04898   0.04141  -0.0112   1.0000   0.1922
  -5.750  -0.6395   0.04637   0.03829  -0.0089   1.0000   0.1758
  -5.500  -0.6287   0.04432   0.03565  -0.0064   1.0000   0.1630
  -5.250  -0.6158   0.04217   0.03295  -0.0041   1.0000   0.1532
  -5.000  -0.5992   0.04029   0.03072  -0.0022   1.0000   0.1468
  -4.750  -0.5814   0.03830   0.02836  -0.0005   1.0000   0.1403
  -4.500  -0.5632   0.03759   0.02696   0.0018   1.0000   0.1346
  -4.250  -0.5425   0.03570   0.02490   0.0030   1.0000   0.1333
  -4.000  -0.5223   0.03442   0.02334   0.0043   1.0000   0.1339
  -3.750  -0.5012   0.03327   0.02196   0.0055   1.0000   0.1346
  -3.500  -0.4781   0.03212   0.02065   0.0066   1.0000   0.1352
  -3.250  -0.4531   0.03079   0.01937   0.0074   1.0000   0.1367
  -3.000  -0.4307   0.02977   0.01845   0.0085   1.0000   0.1424
  -2.750  -0.4108   0.02914   0.01775   0.0100   1.0000   0.1485
  -2.500  -0.3931   0.02840   0.01700   0.0116   1.0000   0.1538
  -2.250  -0.3766   0.02770   0.01625   0.0131   1.0000   0.1639
  -2.000  -0.0441   0.03073   0.02169  -0.0185   1.0000   1.0000
  -1.750  -0.0479   0.03070   0.02159  -0.0156   1.0000   1.0000
  -1.500  -0.0518   0.03064   0.02145  -0.0128   1.0000   1.0000
  -1.250  -0.0560   0.03053   0.02127  -0.0100   1.0000   1.0000
  -1.000  -0.0607   0.03036   0.02104  -0.0071   1.0000   1.0000
  -0.750  -0.0662   0.03014   0.02076  -0.0041   1.0000   1.0000
  -0.500  -0.0732   0.02983   0.02038  -0.0008   1.0000   1.0000
  -0.250  -0.0821   0.02942   0.01993   0.0028   1.0000   1.0000
   0.000  -0.0684   0.02940   0.01979   0.0023   0.9946   1.0000
   0.250  -0.0505   0.02950   0.01977   0.0013   0.9870   1.0000
   0.500  -0.0369   0.02960   0.01975   0.0012   0.9797   1.0000
   0.750  -0.0192   0.02993   0.01993   0.0006   0.9726   1.0000
   1.000   0.0002   0.03039   0.02024  -0.0001   0.9654   1.0000
   1.250   0.0201   0.03094   0.02066  -0.0006   0.9581   1.0000
   1.500   0.0473   0.03177   0.02137  -0.0023   0.9504   1.0000
   1.750   0.0669   0.03241   0.02191  -0.0026   0.9420   1.0000
   2.000   0.1008   0.03341   0.02283  -0.0052   0.9303   1.0000
   2.250   0.1385   0.03444   0.02380  -0.0083   0.9164   1.0000
   2.500   0.1733   0.03538   0.02471  -0.0108   0.9022   1.0000
   2.750   0.1961   0.03614   0.02545  -0.0112   0.8891   1.0000
   3.000   0.2219   0.03703   0.02634  -0.0121   0.8758   1.0000
   3.250   0.2500   0.03798   0.02729  -0.0132   0.8617   1.0000
   3.500   0.2810   0.03892   0.02826  -0.0147   0.8457   1.0000
   3.750   0.3135   0.03982   0.02922  -0.0162   0.8283   1.0000
   4.000   0.3549   0.04063   0.03012  -0.0186   0.8086   1.0000
   4.250   0.3916   0.04129   0.03088  -0.0200   0.7874   1.0000
   4.500   0.4225   0.04181   0.03152  -0.0203   0.7644   1.0000
   4.750   0.4819   0.04174   0.03165  -0.0236   0.7414   1.0000
   5.000   0.5019   0.04220   0.03222  -0.0221   0.7170   1.0000
   5.250   0.5698   0.04123   0.03156  -0.0255   0.6949   1.0000
   5.500   0.5890   0.04149   0.03193  -0.0234   0.6694   1.0000
   5.750   0.6652   0.03905   0.02988  -0.0260   0.6478   1.0000
   6.000   0.6912   0.03848   0.02947  -0.0237   0.6210   1.0000
   6.250   0.7369   0.03660   0.02785  -0.0226   0.5948   1.0000
   6.500   0.7904   0.03397   0.02544  -0.0218   0.5664   1.0000
   6.750   0.8297   0.03213   0.02375  -0.0200   0.5332   1.0000
   7.000   0.8686   0.03045   0.02207  -0.0182   0.4972   1.0000
   7.250   0.8981   0.02969   0.02120  -0.0162   0.4607   1.0000
   7.500   0.9182   0.02977   0.02119  -0.0136   0.4250   1.0000
   8.000   0.9528   0.03068   0.02165  -0.0083   0.3515   1.0000
   8.250   0.9688   0.03170   0.02228  -0.0059   0.3124   1.0000
   8.500   0.9772   0.03328   0.02376  -0.0030   0.2764   1.0000
   8.750   0.9853   0.03498   0.02530   0.0000   0.2404   1.0000
   9.000   0.9971   0.03688   0.02692   0.0024   0.2073   1.0000
   9.250   1.0071   0.03911   0.02916   0.0049   0.1821   1.0000
   9.500   1.0258   0.04148   0.03139   0.0061   0.1625   1.0000
   9.750   1.0376   0.04388   0.03397   0.0080   0.1491   1.0000
  10.000   1.0470   0.04688   0.03729   0.0101   0.1408   1.0000
  10.250   1.0673   0.04971   0.04004   0.0107   0.1318   1.0000
  10.500   1.0600   0.05273   0.04361   0.0142   0.1281   1.0000
  10.750   1.0575   0.05578   0.04699   0.0169   0.1243   1.0000
  11.000   1.0715   0.05900   0.05026   0.0178   0.1199   1.0000
  11.250   1.0658   0.06283   0.05431   0.0201   0.1182   1.0000
  11.500   1.0454   0.06633   0.05812   0.0235   0.1179   1.0000
  11.750   1.0235   0.07003   0.06204   0.0264   0.1179   1.0000
  12.000   0.9990   0.07417   0.06638   0.0282   0.1180   1.0000
  12.250   0.9751   0.07891   0.07127   0.0288   0.1184   1.0000
  12.500   0.7982   0.10347   0.09602   0.0134   0.1434   1.0000
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