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LOCKHEED C-5A BL0 AIRFOIL (c5a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-5A BL0 AIRFOIL (c5a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.06 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c5a-il-50000-n5.txt
Download as CSV file: xf-c5a-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6366   0.09895   0.09099  -0.0473   1.0000   0.0505
 -11.750  -0.6691   0.08996   0.08196  -0.0523   1.0000   0.0495
 -11.500  -0.7049   0.08257   0.07448  -0.0554   1.0000   0.0487
 -11.250  -0.7389   0.07694   0.06869  -0.0561   1.0000   0.0482
 -11.000  -0.7697   0.07265   0.06422  -0.0548   1.0000   0.0477
 -10.750  -0.7977   0.06934   0.06072  -0.0518   1.0000   0.0474
 -10.500  -0.8223   0.06662   0.05781  -0.0475   1.0000   0.0473
 -10.250  -0.8382   0.06372   0.05468  -0.0439   1.0000   0.0472
 -10.000  -0.8477   0.06091   0.05164  -0.0405   1.0000   0.0472
  -9.750  -0.8526   0.05818   0.04867  -0.0374   1.0000   0.0474
  -9.500  -0.8525   0.05566   0.04595  -0.0346   1.0000   0.0479
  -9.250  -0.8494   0.05333   0.04341  -0.0321   1.0000   0.0488
  -9.000  -0.8446   0.05107   0.04092  -0.0296   1.0000   0.0498
  -8.750  -0.8379   0.04881   0.03839  -0.0271   1.0000   0.0510
  -8.500  -0.8284   0.04655   0.03583  -0.0249   1.0000   0.0522
  -8.250  -0.8153   0.04434   0.03329  -0.0229   1.0000   0.0532
  -8.000  -0.7984   0.04223   0.03086  -0.0212   1.0000   0.0542
  -7.750  -0.7782   0.04033   0.02863  -0.0198   1.0000   0.0553
  -7.500  -0.7557   0.03857   0.02677  -0.0189   1.0000   0.0570
  -7.250  -0.7360   0.03718   0.02538  -0.0177   1.0000   0.0599
  -7.000  -0.7156   0.03596   0.02405  -0.0163   1.0000   0.0635
  -6.750  -0.6944   0.03483   0.02268  -0.0148   1.0000   0.0668
  -6.500  -0.6782   0.03360   0.02150  -0.0129   1.0000   0.0701
  -6.250  -0.6643   0.03254   0.02039  -0.0108   1.0000   0.0754
  -6.000  -0.6517   0.03145   0.01925  -0.0084   1.0000   0.0817
  -5.750  -0.6399   0.03035   0.01815  -0.0061   1.0000   0.0897
  -5.500  -0.6284   0.02919   0.01703  -0.0038   1.0000   0.1023
  -5.250  -0.6180   0.02778   0.01578  -0.0014   1.0000   0.1295
  -5.000  -0.6117   0.02571   0.01439   0.0010   1.0000   0.2017
  -4.750  -0.6089   0.02356   0.01361   0.0043   1.0000   0.3939
  -4.500  -0.5973   0.02330   0.01409   0.0086   1.0000   0.5449
  -4.250  -0.5866   0.02389   0.01492   0.0138   1.0000   0.6404
  -4.000  -0.5744   0.02482   0.01588   0.0192   1.0000   0.6963
  -3.750  -0.5581   0.02526   0.01618   0.0227   1.0000   0.7255
  -3.500  -0.5386   0.02565   0.01642   0.0255   1.0000   0.7460
  -3.250  -0.5200   0.02595   0.01656   0.0283   1.0000   0.7668
  -3.000  -0.5020   0.02611   0.01656   0.0308   1.0000   0.7868
  -2.750  -0.4835   0.02618   0.01649   0.0330   1.0000   0.8049
  -2.500  -0.4619   0.02622   0.01637   0.0345   1.0000   0.8188
  -2.250  -0.4396   0.02614   0.01615   0.0354   1.0000   0.8302
  -2.000  -0.4195   0.02596   0.01585   0.0365   1.0000   0.8421
  -1.750  -0.4004   0.02576   0.01553   0.0376   1.0000   0.8545
  -1.500  -0.3774   0.02568   0.01532   0.0381   1.0000   0.8652
  -1.250  -0.3543   0.02558   0.01513   0.0385   1.0000   0.8761
  -1.000  -0.3325   0.02547   0.01493   0.0389   1.0000   0.8877
  -0.750  -0.3092   0.02540   0.01478   0.0390   1.0000   0.8994
  -0.500  -0.2812   0.02543   0.01474   0.0382   1.0000   0.9094
  -0.250  -0.2526   0.02547   0.01472   0.0371   0.9992   0.9202
   0.000  -0.2081   0.02573   0.01490   0.0328   0.9933   0.9287
   0.250  -0.1630   0.02599   0.01511   0.0283   0.9871   0.9365
   0.500  -0.1193   0.02622   0.01531   0.0241   0.9808   0.9447
   0.750  -0.0712   0.02653   0.01560   0.0190   0.9751   0.9519
   1.000  -0.0281   0.02672   0.01581   0.0148   0.9678   0.9596
   1.250   0.0215   0.02701   0.01613   0.0093   0.9618   0.9659
   1.500   0.0659   0.02721   0.01639   0.0049   0.9539   0.9733
   1.750   0.1140   0.02744   0.01670  -0.0003   0.9466   0.9793
   2.000   0.1615   0.02762   0.01699  -0.0053   0.9380   0.9861
   2.250   0.2078   0.02771   0.01721  -0.0100   0.9267   0.9927
   2.500   0.2561   0.02776   0.01741  -0.0149   0.9154   0.9988
   2.750   0.2917   0.02772   0.01751  -0.0173   0.9036   1.0000
   3.000   0.3261   0.02759   0.01753  -0.0192   0.8906   1.0000
   3.250   0.3534   0.02726   0.01734  -0.0193   0.8702   1.0000
   3.500   0.4014   0.02645   0.01675  -0.0222   0.8474   1.0000
   3.750   0.4422   0.02544   0.01593  -0.0233   0.8189   1.0000
   4.000   0.4757   0.02461   0.01528  -0.0232   0.7910   1.0000
   4.250   0.5049   0.02398   0.01484  -0.0225   0.7636   1.0000
   4.500   0.5286   0.02342   0.01443  -0.0208   0.7282   1.0000
   4.750   0.5677   0.02248   0.01345  -0.0205   0.6555   1.0000
   5.000   0.6032   0.02229   0.01261  -0.0197   0.5053   1.0000
   5.250   0.6063   0.02313   0.01262  -0.0150   0.3720   1.0000
   5.500   0.6055   0.02413   0.01303  -0.0102   0.2890   1.0000
   5.750   0.6090   0.02511   0.01365  -0.0064   0.2356   1.0000
   6.000   0.6163   0.02614   0.01437  -0.0034   0.1981   1.0000
   6.250   0.6278   0.02720   0.01525  -0.0011   0.1714   1.0000
   6.500   0.6424   0.02828   0.01618   0.0007   0.1521   1.0000
   6.750   0.6617   0.02935   0.01720   0.0018   0.1386   1.0000
   7.000   0.6868   0.03047   0.01839   0.0021   0.1278   1.0000
   7.250   0.7140   0.03165   0.01959   0.0020   0.1185   1.0000
   7.500   0.7412   0.03284   0.02080   0.0019   0.1106   1.0000
   7.750   0.7736   0.03430   0.02242   0.0011   0.1052   1.0000
   8.000   0.8014   0.03573   0.02401   0.0010   0.0998   1.0000
   8.250   0.8268   0.03722   0.02551   0.0009   0.0951   1.0000
   8.500   0.8515   0.03907   0.02773   0.0013   0.0911   1.0000
   8.750   0.8735   0.04092   0.02981   0.0019   0.0874   1.0000
   9.000   0.8938   0.04259   0.03154   0.0024   0.0838   1.0000
   9.250   0.9095   0.04491   0.03423   0.0039   0.0809   1.0000
   9.500   0.9212   0.04750   0.03728   0.0058   0.0784   1.0000
   9.750   0.9305   0.04987   0.03999   0.0078   0.0755   1.0000
  10.000   0.9409   0.05196   0.04225   0.0094   0.0729   1.0000
  10.250   0.9523   0.05431   0.04471   0.0107   0.0709   1.0000
  10.500   0.9502   0.05751   0.04829   0.0136   0.0697   1.0000
  10.750   0.9386   0.06090   0.05214   0.0172   0.0686   1.0000
  11.000   0.9223   0.06423   0.05583   0.0208   0.0677   1.0000
  11.250   0.9024   0.06776   0.05964   0.0241   0.0670   1.0000
  11.500   0.8796   0.07176   0.06389   0.0264   0.0667   1.0000
  11.750   0.8537   0.07647   0.06881   0.0273   0.0666   1.0000
  12.000   0.8247   0.08223   0.07474   0.0264   0.0669   1.0000
  12.250   0.7939   0.08938   0.08200   0.0234   0.0674   1.0000
  12.500   0.7639   0.09811   0.09080   0.0182   0.0681   1.0000
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