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LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)
Reynolds number: 100,000
Max Cl/Cd: 46.43 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5e-il-100000.txt
Download as CSV file: xf-c5e-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL1256 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5096   0.11077   0.10524  -0.0121   1.0000   0.1090
  -9.500  -0.5005   0.10759   0.10206  -0.0121   1.0000   0.1126
  -9.250  -0.5011   0.10403   0.09854  -0.0144   1.0000   0.1168
  -9.000  -0.5317   0.09971   0.09434  -0.0243   1.0000   0.1201
  -8.750  -0.5693   0.09555   0.09015  -0.0324   1.0000   0.1206
  -8.500  -0.5107   0.09123   0.08591  -0.0221   1.0000   0.1243
  -8.250  -0.5014   0.08816   0.08286  -0.0217   1.0000   0.1280
  -8.000  -0.5103   0.08388   0.07864  -0.0255   1.0000   0.1324
  -7.750  -0.5540   0.07976   0.07435  -0.0345   1.0000   0.1363
  -7.500  -0.5456   0.07422   0.06889  -0.0341   1.0000   0.1388
  -7.250  -0.5245   0.07141   0.06620  -0.0315   1.0000   0.1436
  -7.000  -0.5458   0.06966   0.06409  -0.0342   1.0000   0.1527
  -6.750  -0.5375   0.06434   0.05889  -0.0334   1.0000   0.1556
  -6.500  -0.5247   0.06121   0.05587  -0.0318   1.0000   0.1593
  -6.250  -0.5340   0.05988   0.05410  -0.0316   1.0000   0.1707
  -6.000  -0.5207   0.05548   0.04995  -0.0300   1.0000   0.1738
  -5.750  -0.5127   0.05311   0.04758  -0.0281   1.0000   0.1801
  -5.500  -0.5117   0.05059   0.04493  -0.0266   1.0000   0.1904
  -5.250  -0.5092   0.04896   0.04312  -0.0247   1.0000   0.2050
  -5.000  -0.5000   0.04635   0.04066  -0.0225   1.0000   0.2124
  -4.750  -0.4938   0.04417   0.03843  -0.0207   1.0000   0.2274
  -4.500  -0.4545   0.03671   0.02919  -0.0224   1.0000   0.1179
  -4.250  -0.4330   0.03326   0.02493  -0.0212   1.0000   0.1048
  -4.000  -0.4136   0.03146   0.02286  -0.0203   1.0000   0.1050
  -3.750  -0.3929   0.02990   0.02100  -0.0195   1.0000   0.1057
  -3.500  -0.3708   0.02812   0.01899  -0.0190   1.0000   0.1059
  -3.250  -0.3474   0.02643   0.01714  -0.0188   1.0000   0.1066
  -3.000  -0.3236   0.02514   0.01576  -0.0186   1.0000   0.1083
  -2.750  -0.2967   0.02431   0.01492  -0.0190   0.9989   0.1121
  -2.500  -0.2532   0.02351   0.01393  -0.0222   0.9937   0.1187
  -2.250  -0.2130   0.02233   0.01273  -0.0248   0.9879   0.1241
  -2.000  -0.1692   0.02173   0.01211  -0.0281   0.9827   0.1348
  -1.750  -0.1318   0.02088   0.01142  -0.0303   0.9757   0.1468
  -1.500  -0.0884   0.02016   0.01085  -0.0335   0.9706   0.1677
  -1.250  -0.0541   0.01937   0.01033  -0.0352   0.9625   0.1978
  -1.000  -0.0103   0.01809   0.00954  -0.0391   0.9575   0.2804
  -0.750   0.0010   0.01683   0.01038  -0.0339   0.9490   0.7910
  -0.500   0.0201   0.01724   0.01090  -0.0296   0.9408   0.8672
  -0.250   0.0373   0.01748   0.01116  -0.0254   0.9308   0.9162
   0.000   0.0917   0.01768   0.01127  -0.0288   0.9271   0.9557
   0.250   0.1844   0.01780   0.01128  -0.0406   0.9268   0.9778
   0.500   0.2715   0.01767   0.01109  -0.0521   0.9243   0.9938
   0.750   0.3266   0.01748   0.01089  -0.0578   0.9154   1.0000
   1.000   0.3607   0.01736   0.01076  -0.0595   0.9037   1.0000
   1.250   0.4001   0.01707   0.01047  -0.0615   0.8930   1.0000
   1.500   0.4288   0.01685   0.01025  -0.0615   0.8787   1.0000
   1.750   0.4519   0.01670   0.01011  -0.0603   0.8632   1.0000
   2.000   0.4728   0.01656   0.00997  -0.0587   0.8473   1.0000
   2.250   0.4921   0.01646   0.00988  -0.0566   0.8314   1.0000
   2.500   0.5113   0.01627   0.00969  -0.0543   0.8145   1.0000
   2.750   0.5312   0.01594   0.00933  -0.0516   0.7958   1.0000
   3.000   0.5476   0.01570   0.00906  -0.0485   0.7738   1.0000
   3.250   0.5660   0.01542   0.00875  -0.0456   0.7513   1.0000
   3.500   0.5871   0.01510   0.00837  -0.0431   0.7287   1.0000
   3.750   0.6061   0.01491   0.00818  -0.0406   0.7012   1.0000
   4.000   0.6275   0.01469   0.00792  -0.0385   0.6708   1.0000
   4.250   0.6493   0.01451   0.00772  -0.0364   0.6335   1.0000
   4.500   0.6691   0.01441   0.00744  -0.0338   0.5675   1.0000
   4.750   0.6748   0.01560   0.00733  -0.0291   0.3299   1.0000
   5.000   0.6816   0.01787   0.00845  -0.0262   0.2048   1.0000
   5.250   0.6981   0.01931   0.00953  -0.0245   0.1736   1.0000
   5.500   0.7189   0.02050   0.01057  -0.0233   0.1560   1.0000
   5.750   0.7419   0.02172   0.01156  -0.0226   0.1445   1.0000
   6.000   0.7670   0.02272   0.01251  -0.0221   0.1353   1.0000
   6.250   0.7937   0.02410   0.01378  -0.0219   0.1294   1.0000
   6.500   0.8208   0.02526   0.01501  -0.0216   0.1243   1.0000
   6.750   0.8479   0.02662   0.01627  -0.0216   0.1195   1.0000
   7.000   0.8746   0.02816   0.01790  -0.0214   0.1153   1.0000
   7.250   0.9006   0.02959   0.01954  -0.0210   0.1121   1.0000
   7.500   0.9262   0.03109   0.02113  -0.0207   0.1087   1.0000
   7.750   0.9517   0.03310   0.02306  -0.0207   0.1051   1.0000
   8.000   0.9730   0.03491   0.02528  -0.0197   0.1028   1.0000
   8.250   0.9933   0.03686   0.02762  -0.0186   0.1001   1.0000
   8.500   1.0133   0.03882   0.02983  -0.0177   0.0973   1.0000
   8.750   1.0341   0.04096   0.03209  -0.0171   0.0951   1.0000
   9.000   1.0547   0.04414   0.03527  -0.0169   0.0929   1.0000
   9.250   1.0643   0.04696   0.03864  -0.0149   0.0917   1.0000
   9.500   1.0720   0.05028   0.04244  -0.0130   0.0910   1.0000
   9.750   1.0787   0.05415   0.04668  -0.0113   0.0912   1.0000
  10.000   1.0844   0.05838   0.05119  -0.0099   0.0918   1.0000
  10.250   1.0950   0.06343   0.05636  -0.0094   0.0927   1.0000
  10.500   1.0288   0.07157   0.06565  -0.0044   0.1025   1.0000
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