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LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il)
Reynolds number: 100,000
Max Cl/Cd: 41.51 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5a-il-100000.txt
Download as CSV file: xf-c5a-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL0 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5812   0.09676   0.09154  -0.0318   1.0000   0.1838
  -9.750  -0.6088   0.09145   0.08634  -0.0337   1.0000   0.1937
  -9.500  -0.6090   0.08777   0.08269  -0.0330   1.0000   0.1967
  -9.250  -0.6433   0.08260   0.07765  -0.0342   1.0000   0.2086
  -9.000  -0.8604   0.05969   0.05346  -0.0293   1.0000   0.0947
  -8.750  -0.8721   0.05356   0.04658  -0.0243   1.0000   0.0773
  -8.500  -0.8689   0.04996   0.04276  -0.0215   1.0000   0.0754
  -8.250  -0.8658   0.04630   0.03874  -0.0184   1.0000   0.0727
  -8.000  -0.8659   0.04306   0.03451  -0.0136   1.0000   0.0677
  -7.750  -0.8501   0.04059   0.03177  -0.0117   1.0000   0.0665
  -7.500  -0.8340   0.03771   0.02862  -0.0100   1.0000   0.0658
  -7.250  -0.8162   0.03531   0.02594  -0.0083   1.0000   0.0654
  -7.000  -0.7965   0.03323   0.02360  -0.0069   1.0000   0.0654
  -6.750  -0.7753   0.03143   0.02156  -0.0055   1.0000   0.0657
  -6.500  -0.7534   0.02998   0.01989  -0.0042   1.0000   0.0667
  -6.250  -0.7302   0.02806   0.01800  -0.0035   1.0000   0.0693
  -6.000  -0.7090   0.02683   0.01681  -0.0024   1.0000   0.0726
  -5.750  -0.6878   0.02570   0.01566  -0.0011   1.0000   0.0757
  -5.500  -0.6677   0.02471   0.01460   0.0004   1.0000   0.0790
  -5.250  -0.6510   0.02345   0.01349   0.0021   1.0000   0.0846
  -5.000  -0.6335   0.02253   0.01260   0.0037   1.0000   0.0939
  -4.750  -0.6159   0.02153   0.01172   0.0053   1.0000   0.1093
  -4.500  -0.6034   0.01892   0.01015   0.0068   1.0000   0.2291
  -4.250  -0.5973   0.01706   0.01039   0.0112   1.0000   0.6045
  -4.000  -0.5799   0.01748   0.01085   0.0143   1.0000   0.6661
  -3.750  -0.5628   0.01801   0.01136   0.0175   1.0000   0.7051
  -3.500  -0.5480   0.01873   0.01209   0.0217   1.0000   0.7379
  -3.250  -0.5362   0.01965   0.01304   0.0270   1.0000   0.7668
  -3.000  -0.5236   0.02032   0.01369   0.0317   1.0000   0.7914
  -2.750  -0.5089   0.02075   0.01406   0.0355   1.0000   0.8094
  -2.500  -0.4916   0.02087   0.01409   0.0379   1.0000   0.8242
  -2.250  -0.4740   0.02091   0.01403   0.0400   1.0000   0.8386
  -2.000  -0.4573   0.02099   0.01404   0.0424   1.0000   0.8537
  -1.750  -0.4416   0.02111   0.01411   0.0452   1.0000   0.8697
  -1.500  -0.4246   0.02119   0.01414   0.0477   1.0000   0.8854
  -1.250  -0.4042   0.02124   0.01411   0.0491   1.0000   0.8988
  -1.000  -0.3800   0.02129   0.01410   0.0496   1.0000   0.9109
  -0.750  -0.3534   0.02135   0.01410   0.0493   1.0000   0.9230
  -0.500  -0.3248   0.02142   0.01410   0.0483   1.0000   0.9350
  -0.250  -0.2924   0.02157   0.01420   0.0464   1.0000   0.9459
   0.000  -0.2508   0.02187   0.01445   0.0426   1.0000   0.9539
   0.250  -0.2118   0.02216   0.01469   0.0391   1.0000   0.9632
   0.500  -0.1658   0.02257   0.01508   0.0341   1.0000   0.9707
   0.750  -0.1196   0.02300   0.01549   0.0289   1.0000   0.9777
   1.000  -0.0632   0.02354   0.01603   0.0217   0.9954   0.9836
   1.250  -0.0004   0.02405   0.01656   0.0133   0.9873   0.9872
   1.500   0.0631   0.02445   0.01701   0.0050   0.9777   0.9909
   1.750   0.1238   0.02473   0.01735  -0.0028   0.9677   0.9949
   2.000   0.1851   0.02489   0.01760  -0.0105   0.9572   0.9986
   2.250   0.2416   0.02481   0.01761  -0.0169   0.9441   1.0000
   2.500   0.3026   0.02433   0.01725  -0.0235   0.9276   1.0000
   2.750   0.3656   0.02356   0.01664  -0.0300   0.9113   1.0000
   3.000   0.4232   0.02270   0.01594  -0.0353   0.8960   1.0000
   3.250   0.5013   0.02102   0.01449  -0.0432   0.8785   1.0000
   3.500   0.5596   0.01918   0.01285  -0.0469   0.8518   1.0000
   3.750   0.6003   0.01791   0.01171  -0.0478   0.8199   1.0000
   4.000   0.6377   0.01690   0.01075  -0.0482   0.7712   1.0000
   4.250   0.6741   0.01624   0.00990  -0.0482   0.6790   1.0000
   4.500   0.6917   0.01673   0.00947  -0.0450   0.4994   1.0000
   4.750   0.6843   0.01845   0.00984  -0.0387   0.2901   1.0000
   5.000   0.6838   0.01986   0.01055  -0.0341   0.2075   1.0000
   5.250   0.6875   0.02090   0.01128  -0.0300   0.1748   1.0000
   5.500   0.6950   0.02171   0.01195  -0.0266   0.1566   1.0000
   5.750   0.7055   0.02249   0.01264  -0.0237   0.1453   1.0000
   6.000   0.7210   0.02353   0.01346  -0.0219   0.1371   1.0000
   6.250   0.7369   0.02425   0.01429  -0.0197   0.1305   1.0000
   6.500   0.7567   0.02533   0.01524  -0.0186   0.1240   1.0000
   6.750   0.7754   0.02632   0.01635  -0.0170   0.1190   1.0000
   7.000   0.7955   0.02739   0.01753  -0.0157   0.1148   1.0000
   7.250   0.8176   0.02872   0.01880  -0.0150   0.1104   1.0000
   7.500   0.8373   0.03014   0.02042  -0.0136   0.1065   1.0000
   7.750   0.8571   0.03157   0.02211  -0.0121   0.1032   1.0000
   8.000   0.8783   0.03298   0.02362  -0.0112   0.0993   1.0000
   8.250   0.9008   0.03533   0.02597  -0.0109   0.0957   1.0000
   8.500   0.9149   0.03717   0.02832  -0.0084   0.0936   1.0000
   8.750   0.9278   0.03929   0.03088  -0.0060   0.0907   1.0000
   9.000   0.9409   0.04157   0.03348  -0.0039   0.0882   1.0000
   9.250   0.9528   0.04425   0.03646  -0.0018   0.0867   1.0000
   9.500   0.9714   0.04687   0.03905  -0.0014   0.0839   1.0000
   9.750   0.9738   0.05083   0.04335   0.0014   0.0825   1.0000
  10.000   0.9717   0.05418   0.04716   0.0050   0.0821   1.0000
  10.250   0.9709   0.05846   0.05176   0.0077   0.0824   1.0000
  10.500   0.9726   0.06328   0.05681   0.0097   0.0830   1.0000
  10.750   0.8897   0.06898   0.06349   0.0201   0.0916   1.0000
  11.000   0.8759   0.07366   0.06828   0.0220   0.0939   1.0000
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