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KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.74 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kc135a-il-50000-n5.txt
Download as CSV file: xf-kc135a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 BL52.44 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5342   0.10009   0.09235  -0.0449   1.0000   0.0572
 -12.000  -0.5482   0.09400   0.08625  -0.0481   1.0000   0.0569
 -11.750  -0.5658   0.08815   0.08037  -0.0512   1.0000   0.0566
 -11.500  -0.5835   0.08292   0.07510  -0.0535   1.0000   0.0561
 -11.250  -0.6056   0.07806   0.07015  -0.0553   1.0000   0.0559
 -11.000  -0.6267   0.07393   0.06592  -0.0559   1.0000   0.0557
 -10.750  -0.6462   0.07044   0.06232  -0.0552   1.0000   0.0555
 -10.500  -0.6661   0.06749   0.05925  -0.0531   1.0000   0.0555
 -10.250  -0.6841   0.06491   0.05653  -0.0500   1.0000   0.0555
 -10.000  -0.6975   0.06225   0.05368  -0.0471   1.0000   0.0557
  -9.750  -0.7079   0.05967   0.05088  -0.0440   1.0000   0.0559
  -9.500  -0.7150   0.05718   0.04814  -0.0408   1.0000   0.0562
  -9.250  -0.7194   0.05479   0.04550  -0.0376   1.0000   0.0564
  -9.000  -0.7207   0.05248   0.04293  -0.0344   1.0000   0.0567
  -8.750  -0.7190   0.05030   0.04049  -0.0314   1.0000   0.0569
  -8.500  -0.7164   0.04827   0.03820  -0.0282   1.0000   0.0572
  -8.250  -0.7113   0.04628   0.03608  -0.0254   1.0000   0.0579
  -8.000  -0.7041   0.04469   0.03447  -0.0229   1.0000   0.0591
  -7.750  -0.6991   0.04337   0.03310  -0.0200   1.0000   0.0603
  -7.500  -0.6954   0.04219   0.03180  -0.0168   1.0000   0.0617
  -7.250  -0.6618   0.04012   0.02942  -0.0187   0.9909   0.0642
  -7.000  -0.6218   0.03813   0.02705  -0.0211   0.9817   0.0665
  -6.750  -0.5799   0.03633   0.02528  -0.0239   0.9737   0.0705
  -6.500  -0.5374   0.03494   0.02382  -0.0263   0.9652   0.0747
  -6.250  -0.4914   0.03365   0.02243  -0.0290   0.9588   0.0801
  -6.000  -0.4560   0.03253   0.02132  -0.0306   0.9484   0.0861
  -5.750  -0.4232   0.03143   0.02011  -0.0319   0.9381   0.0928
  -5.500  -0.3925   0.03023   0.01889  -0.0334   0.9285   0.1012
  -5.250  -0.3705   0.02912   0.01773  -0.0334   0.9160   0.1100
  -5.000  -0.3485   0.02796   0.01655  -0.0334   0.9046   0.1240
  -4.750  -0.3282   0.02648   0.01522  -0.0334   0.8944   0.1511
  -4.500  -0.3348   0.02402   0.01452  -0.0292   0.8809   0.3687
  -4.250  -0.3224   0.02438   0.01531  -0.0249   0.8702   0.5491
  -4.000  -0.3022   0.02491   0.01573  -0.0221   0.8610   0.6046
  -3.750  -0.2828   0.02549   0.01624  -0.0191   0.8512   0.6421
  -3.500  -0.2529   0.02652   0.01729  -0.0164   0.8442   0.6841
  -3.250  -0.2267   0.02726   0.01793  -0.0140   0.8363   0.7148
  -3.000  -0.1929   0.02741   0.01792  -0.0143   0.8287   0.7252
  -2.750  -0.1718   0.02703   0.01733  -0.0138   0.8210   0.7336
  -2.500  -0.1438   0.02697   0.01712  -0.0139   0.8125   0.7388
  -2.250  -0.1132   0.02673   0.01669  -0.0146   0.8066   0.7458
  -2.000  -0.0959   0.02664   0.01649  -0.0134   0.7972   0.7534
  -1.750  -0.0636   0.02655   0.01626  -0.0142   0.7911   0.7595
  -1.500  -0.0461   0.02644   0.01604  -0.0131   0.7832   0.7686
  -1.250  -0.0153   0.02647   0.01598  -0.0137   0.7764   0.7744
  -1.000   0.0161   0.02634   0.01574  -0.0144   0.7713   0.7822
  -0.750   0.0335   0.02650   0.01587  -0.0132   0.7625   0.7903
  -0.500   0.0630   0.02650   0.01580  -0.0136   0.7568   0.7982
  -0.250   0.0863   0.02658   0.01583  -0.0133   0.7502   0.8070
   0.000   0.1114   0.02675   0.01599  -0.0131   0.7428   0.8155
   0.250   0.1419   0.02675   0.01593  -0.0137   0.7378   0.8247
   0.500   0.1643   0.02705   0.01625  -0.0133   0.7300   0.8342
   0.750   0.1932   0.02719   0.01638  -0.0138   0.7235   0.8440
   1.000   0.2296   0.02720   0.01636  -0.0152   0.7191   0.8535
   1.250   0.2510   0.02768   0.01690  -0.0150   0.7099   0.8646
   1.500   0.2840   0.02776   0.01698  -0.0161   0.7042   0.8761
   1.750   0.3171   0.02810   0.01736  -0.0176   0.6969   0.8867
   2.000   0.3508   0.02837   0.01767  -0.0192   0.6895   0.8980
   2.250   0.3906   0.02834   0.01765  -0.0212   0.6845   0.9099
   2.500   0.4227   0.02892   0.01833  -0.0232   0.6745   0.9221
   2.750   0.4677   0.02888   0.01833  -0.0263   0.6683   0.9322
   3.000   0.5004   0.02931   0.01886  -0.0283   0.6581   0.9464
   3.250   0.5448   0.02910   0.01868  -0.0310   0.6505   0.9582
   3.500   0.5808   0.02937   0.01906  -0.0335   0.6383   0.9730
   3.750   0.6241   0.02918   0.01893  -0.0364   0.6278   0.9857
   4.000   0.6688   0.02892   0.01875  -0.0397   0.6167   0.9990
   4.250   0.6686   0.02932   0.01919  -0.0359   0.6052   1.0000
   4.500   0.6850   0.02914   0.01899  -0.0337   0.5966   1.0000
   4.750   0.6892   0.02949   0.01938  -0.0302   0.5850   1.0000
   5.000   0.6972   0.02979   0.01970  -0.0271   0.5735   1.0000
   5.250   0.7218   0.02945   0.01936  -0.0258   0.5640   1.0000
   5.500   0.7305   0.02979   0.01975  -0.0228   0.5511   1.0000
   5.750   0.7409   0.03008   0.02010  -0.0199   0.5379   1.0000
   6.000   0.7563   0.03016   0.02022  -0.0176   0.5251   1.0000
   6.250   0.7759   0.03004   0.02014  -0.0157   0.5121   1.0000
   6.500   0.7962   0.02988   0.02000  -0.0138   0.4983   1.0000
   6.750   0.8094   0.03003   0.02022  -0.0112   0.4825   1.0000
   7.000   0.8224   0.03019   0.02043  -0.0086   0.4660   1.0000
   7.250   0.8324   0.03050   0.02078  -0.0058   0.4483   1.0000
   7.500   0.8408   0.03093   0.02126  -0.0029   0.4295   1.0000
   7.750   0.8509   0.03130   0.02167  -0.0001   0.4103   1.0000
   8.000   0.8644   0.03155   0.02190   0.0023   0.3912   1.0000
   8.250   0.8790   0.03177   0.02205   0.0046   0.3725   1.0000
   8.500   0.8921   0.03216   0.02234   0.0069   0.3543   1.0000
   8.750   0.9009   0.03287   0.02300   0.0095   0.3366   1.0000
   9.000   0.9100   0.03368   0.02375   0.0118   0.3198   1.0000
   9.250   0.9197   0.03459   0.02459   0.0139   0.3042   1.0000
   9.500   0.9292   0.03557   0.02552   0.0159   0.2893   1.0000
   9.750   0.9394   0.03662   0.02655   0.0177   0.2754   1.0000
  10.000   0.9463   0.03791   0.02787   0.0195   0.2619   1.0000
  10.250   0.9535   0.03926   0.02925   0.0211   0.2491   1.0000
  10.500   0.9615   0.04061   0.03062   0.0226   0.2370   1.0000
  10.750   0.9695   0.04195   0.03194   0.0240   0.2249   1.0000
  11.000   0.9757   0.04342   0.03342   0.0253   0.2131   1.0000
  11.250   0.9771   0.04533   0.03543   0.0266   0.2018   1.0000
  11.500   0.9797   0.04715   0.03729   0.0277   0.1909   1.0000
  11.750   0.9843   0.04879   0.03888   0.0287   0.1803   1.0000
  12.000   0.9821   0.05117   0.04141   0.0294   0.1701   1.0000
  12.250   0.9819   0.05347   0.04380   0.0301   0.1604   1.0000
  12.500   0.9855   0.05534   0.04560   0.0307   0.1514   1.0000
  12.750   0.9806   0.05838   0.04886   0.0308   0.1426   1.0000
  13.000   0.9813   0.06081   0.05131   0.0311   0.1347   1.0000
  13.250   0.9786   0.06373   0.05434   0.0311   0.1270   1.0000
  13.500   0.9769   0.06671   0.05740   0.0310   0.1203   1.0000
  13.750   0.9735   0.06989   0.06067   0.0307   0.1137   1.0000
  14.000   0.9707   0.07318   0.06403   0.0303   0.1081   1.0000
  14.250   0.9628   0.07738   0.06843   0.0294   0.1031   1.0000
  14.500   0.9685   0.07947   0.07041   0.0294   0.0981   1.0000
  14.750   0.9498   0.08573   0.07700   0.0272   0.0949   1.0000
  15.000   0.9338   0.09176   0.08324   0.0249   0.0918   1.0000
  15.250   0.9330   0.09525   0.08676   0.0239   0.0883   1.0000
  15.500   0.9226   0.10068   0.09228   0.0218   0.0859   1.0000
  15.750   0.8808   0.11276   0.10463   0.0156   0.0853   1.0000
  16.000   0.8044   0.13504   0.12700   0.0037   0.0848   1.0000
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