Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)
Reynolds number: 200,000
Max Cl/Cd: 59.57 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5e-il-200000.txt
Download as CSV file: xf-c5e-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4465   0.08804   0.08435  -0.0323   1.0000   0.0678
  -9.250  -0.4256   0.08623   0.08254  -0.0286   1.0000   0.0689
  -9.000  -0.5701   0.08597   0.08202  -0.0369   1.0000   0.0670
  -8.750  -0.5893   0.08024   0.07618  -0.0398   1.0000   0.0674
  -8.500  -0.5659   0.07634   0.07245  -0.0375   1.0000   0.0684
  -8.250  -0.5541   0.07387   0.07003  -0.0364   1.0000   0.0694
  -8.000  -0.5486   0.07100   0.06716  -0.0365   1.0000   0.0707
  -7.750  -0.5471   0.06768   0.06379  -0.0371   1.0000   0.0726
  -7.500  -0.5698   0.06459   0.06008  -0.0389   1.0000   0.0784
  -7.250  -0.5683   0.05843   0.05394  -0.0385   1.0000   0.0795
  -7.000  -0.5563   0.05550   0.05112  -0.0374   1.0000   0.0806
  -6.750  -0.5453   0.05349   0.04916  -0.0359   1.0000   0.0823
  -6.500  -0.5370   0.05160   0.04724  -0.0343   1.0000   0.0855
  -6.250  -0.5434   0.04880   0.04388  -0.0316   1.0000   0.0925
  -6.000  -0.5362   0.04636   0.04159  -0.0295   1.0000   0.0939
  -5.750  -0.5310   0.04487   0.04016  -0.0270   1.0000   0.0958
  -5.500  -0.5180   0.03235   0.02600  -0.0264   0.9977   0.0680
  -5.250  -0.4815   0.02933   0.02276  -0.0289   0.9941   0.0658
  -5.000  -0.4458   0.02660   0.01962  -0.0310   0.9896   0.0662
  -4.750  -0.4087   0.02412   0.01680  -0.0333   0.9855   0.0661
  -4.500  -0.3698   0.02219   0.01456  -0.0356   0.9821   0.0664
  -4.250  -0.3336   0.02090   0.01302  -0.0373   0.9762   0.0672
  -4.000  -0.2958   0.01904   0.01111  -0.0397   0.9727   0.0691
  -3.750  -0.2580   0.01830   0.01040  -0.0419   0.9677   0.0721
  -3.500  -0.2203   0.01752   0.00955  -0.0439   0.9621   0.0753
  -3.250  -0.1790   0.01675   0.00869  -0.0465   0.9587   0.0782
  -3.000  -0.1445   0.01573   0.00777  -0.0480   0.9526   0.0823
  -2.750  -0.1079   0.01524   0.00731  -0.0497   0.9464   0.0886
  -2.500  -0.0705   0.01452   0.00666  -0.0516   0.9418   0.0960
  -2.250  -0.0403   0.01415   0.00630  -0.0520   0.9323   0.1048
  -2.000  -0.0055   0.01359   0.00583  -0.0533   0.9266   0.1201
  -1.750   0.0213   0.01302   0.00542  -0.0532   0.9163   0.1419
  -1.500   0.0520   0.01250   0.00505  -0.0537   0.9092   0.1748
  -1.250   0.0784   0.01204   0.00477  -0.0535   0.8990   0.2168
  -1.000   0.0971   0.01031   0.00464  -0.0523   0.8901   0.6421
  -0.750   0.1201   0.01020   0.00480  -0.0502   0.8805   0.7311
  -0.500   0.1427   0.01028   0.00497  -0.0482   0.8697   0.7739
  -0.250   0.1657   0.01037   0.00508  -0.0461   0.8599   0.8068
   0.000   0.1871   0.01047   0.00521  -0.0438   0.8480   0.8324
   0.250   0.2095   0.01055   0.00528  -0.0418   0.8364   0.8496
   0.500   0.2326   0.01060   0.00529  -0.0400   0.8264   0.8654
   0.750   0.2549   0.01063   0.00532  -0.0381   0.8149   0.8806
   1.000   0.2769   0.01065   0.00534  -0.0363   0.8038   0.8957
   1.250   0.2991   0.01064   0.00529  -0.0342   0.7941   0.9105
   1.500   0.3206   0.01061   0.00528  -0.0322   0.7825   0.9268
   1.750   0.3448   0.01056   0.00523  -0.0307   0.7704   0.9430
   2.000   0.3753   0.01048   0.00511  -0.0304   0.7554   0.9579
   2.250   0.4124   0.01038   0.00494  -0.0316   0.7350   0.9709
   2.500   0.4530   0.01028   0.00478  -0.0338   0.7141   0.9789
   2.750   0.4930   0.01023   0.00469  -0.0362   0.6954   0.9857
   3.000   0.5332   0.01017   0.00460  -0.0387   0.6689   0.9932
   3.250   0.5726   0.01013   0.00449  -0.0410   0.6363   1.0000
   3.500   0.5914   0.01015   0.00442  -0.0394   0.6060   1.0000
   3.750   0.6093   0.01026   0.00439  -0.0376   0.5684   1.0000
   4.000   0.6261   0.01051   0.00442  -0.0356   0.5123   1.0000
   4.250   0.6390   0.01130   0.00457  -0.0331   0.3823   1.0000
   4.500   0.6481   0.01310   0.00529  -0.0307   0.1948   1.0000
   4.750   0.6672   0.01418   0.00599  -0.0297   0.1459   1.0000
   5.000   0.6887   0.01502   0.00666  -0.0289   0.1221   1.0000
   5.250   0.7114   0.01576   0.00732  -0.0282   0.1092   1.0000
   5.500   0.7343   0.01650   0.00797  -0.0275   0.1019   1.0000
   5.750   0.7583   0.01711   0.00856  -0.0270   0.0966   1.0000
   6.000   0.7805   0.01806   0.00937  -0.0262   0.0924   1.0000
   6.250   0.8051   0.01868   0.01006  -0.0257   0.0890   1.0000
   6.500   0.8294   0.01940   0.01076  -0.0252   0.0857   1.0000
   6.750   0.8536   0.02029   0.01159  -0.0248   0.0831   1.0000
   7.000   0.8783   0.02160   0.01286  -0.0244   0.0805   1.0000
   7.250   0.9034   0.02227   0.01364  -0.0240   0.0781   1.0000
   7.500   0.9283   0.02306   0.01448  -0.0236   0.0752   1.0000
   7.750   0.9527   0.02388   0.01527  -0.0233   0.0724   1.0000
   8.000   0.9779   0.02545   0.01682  -0.0232   0.0698   1.0000
   8.250   1.0015   0.02621   0.01777  -0.0225   0.0676   1.0000
   8.500   1.0253   0.02723   0.01891  -0.0220   0.0653   1.0000
   8.750   1.0488   0.02829   0.02004  -0.0216   0.0633   1.0000
   9.000   1.0727   0.02968   0.02141  -0.0213   0.0615   1.0000
   9.250   1.0939   0.03169   0.02364  -0.0207   0.0598   1.0000
   9.500   1.1129   0.03323   0.02550  -0.0195   0.0581   1.0000
   9.750   1.1315   0.03488   0.02737  -0.0184   0.0563   1.0000
  10.000   1.1504   0.03648   0.02913  -0.0176   0.0549   1.0000
  10.250   1.1688   0.03820   0.03096  -0.0167   0.0538   1.0000
  10.500   1.1855   0.04037   0.03325  -0.0159   0.0529   1.0000
  10.750   1.1967   0.04396   0.03706  -0.0147   0.0522   1.0000
  11.000   1.2003   0.04786   0.04132  -0.0127   0.0519   1.0000
  11.250   1.2001   0.05126   0.04512  -0.0104   0.0518   1.0000
  11.500   1.1963   0.05513   0.04931  -0.0081   0.0518   1.0000
  11.750   1.1913   0.05959   0.05402  -0.0061   0.0520   1.0000
  12.000   1.1820   0.06247   0.05719  -0.0034   0.0523   1.0000
  12.250   0.9737   0.08758   0.08368  -0.0069   0.0634   1.0000
  12.500   0.9906   0.08817   0.08422  -0.0058   0.0622   1.0000
  12.750   1.0280   0.08748   0.08338  -0.0025   0.0613   1.0000
  13.000   0.6356   0.13679   0.13319  -0.0263   0.0865   1.0000
  13.250   0.6348   0.13964   0.13605  -0.0270   0.0847   1.0000
<< Back to LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)

Polar data table (+)

Polar graphs


<< Back to LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)