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 BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.85 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5d-il-1000000.txt
Download as CSV file: xf-c5d-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL758.6 AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7664   0.03495   0.03252  -0.0729   1.0000   0.0161
 -12.000  -0.8909   0.04296   0.04020  -0.0681   1.0000   0.0159
 -11.750  -0.9200   0.04161   0.03875  -0.0615   1.0000   0.0159
 -11.500  -0.9392   0.04030   0.03732  -0.0558   0.9996   0.0158
 -11.250  -0.9260   0.03775   0.03458  -0.0568   0.9976   0.0157
 -11.000  -0.9101   0.03571   0.03236  -0.0574   0.9959   0.0156
 -10.750  -0.8911   0.03386   0.03035  -0.0582   0.9947   0.0156
 -10.500  -0.8860   0.02965   0.02581  -0.0577   0.9921   0.0154
 -10.250  -0.8718   0.02670   0.02256  -0.0576   0.9897   0.0153
 -10.000  -0.8515   0.02453   0.02015  -0.0579   0.9881   0.0152
  -9.750  -0.8271   0.02301   0.01845  -0.0584   0.9870   0.0153
  -9.500  -0.8015   0.02154   0.01680  -0.0591   0.9861   0.0153
  -9.250  -0.7751   0.02000   0.01509  -0.0599   0.9854   0.0152
  -9.000  -0.7509   0.01876   0.01371  -0.0599   0.9836   0.0152
  -8.750  -0.7280   0.01771   0.01255  -0.0595   0.9809   0.0152
  -8.500  -0.7015   0.01675   0.01149  -0.0598   0.9793   0.0152
  -8.250  -0.6734   0.01587   0.01052  -0.0604   0.9781   0.0152
  -8.000  -0.6441   0.01509   0.00965  -0.0612   0.9771   0.0152
  -7.750  -0.6137   0.01437   0.00887  -0.0622   0.9764   0.0153
  -7.500  -0.5826   0.01373   0.00817  -0.0634   0.9758   0.0153
  -7.250  -0.5511   0.01316   0.00754  -0.0645   0.9752   0.0154
  -7.000  -0.5199   0.01265   0.00699  -0.0656   0.9746   0.0155
  -6.750  -0.4978   0.01205   0.00633  -0.0646   0.9711   0.0158
  -6.500  -0.4711   0.01152   0.00575  -0.0646   0.9685   0.0163
  -6.250  -0.4412   0.01110   0.00532  -0.0653   0.9667   0.0169
  -6.000  -0.4103   0.01074   0.00495  -0.0661   0.9651   0.0177
  -5.750  -0.3792   0.01042   0.00461  -0.0669   0.9636   0.0189
  -5.500  -0.3492   0.01003   0.00423  -0.0675   0.9622   0.0218
  -5.250  -0.3258   0.00979   0.00399  -0.0666   0.9582   0.0254
  -5.000  -0.2991   0.00959   0.00382  -0.0664   0.9553   0.0288
  -4.750  -0.2711   0.00933   0.00357  -0.0665   0.9529   0.0324
  -4.500  -0.2420   0.00913   0.00338  -0.0668   0.9509   0.0354
  -4.250  -0.2133   0.00889   0.00314  -0.0670   0.9487   0.0391
  -4.000  -0.1886   0.00870   0.00297  -0.0664   0.9444   0.0430
  -3.750  -0.1620   0.00848   0.00277  -0.0661   0.9406   0.0492
  -3.500  -0.1345   0.00822   0.00257  -0.0661   0.9377   0.0619
  -3.250  -0.1075   0.00788   0.00239  -0.0660   0.9350   0.0972
  -3.000  -0.0807   0.00767   0.00228  -0.0659   0.9317   0.1244
  -2.750  -0.0546   0.00748   0.00215  -0.0655   0.9271   0.1432
  -2.500  -0.0276   0.00722   0.00201  -0.0654   0.9230   0.1749
  -2.250  -0.0007   0.00687   0.00186  -0.0653   0.9195   0.2332
  -2.000   0.0237   0.00637   0.00173  -0.0649   0.9153   0.3368
  -1.750   0.0454   0.00559   0.00158  -0.0640   0.9104   0.5218
  -1.500   0.0712   0.00526   0.00151  -0.0636   0.9061   0.6070
  -1.250   0.0980   0.00507   0.00147  -0.0633   0.9012   0.6559
  -1.000   0.1246   0.00496   0.00144  -0.0629   0.8945   0.6892
  -0.750   0.1524   0.00487   0.00137  -0.0627   0.8870   0.7131
  -0.500   0.1790   0.00480   0.00132  -0.0622   0.8759   0.7353
  -0.250   0.2056   0.00473   0.00129  -0.0618   0.8640   0.7550
   0.000   0.2327   0.00470   0.00127  -0.0614   0.8526   0.7719
   0.250   0.2594   0.00469   0.00124  -0.0610   0.8354   0.7857
   0.500   0.2859   0.00470   0.00122  -0.0605   0.8168   0.7985
   0.750   0.3124   0.00472   0.00122  -0.0600   0.7983   0.8102
   1.000   0.3386   0.00476   0.00123  -0.0595   0.7770   0.8216
   1.250   0.3639   0.00486   0.00124  -0.0589   0.7491   0.8338
   1.500   0.3881   0.00499   0.00129  -0.0579   0.7142   0.8460
   1.750   0.4112   0.00518   0.00137  -0.0568   0.6752   0.8599
   2.000   0.4336   0.00543   0.00146  -0.0555   0.6293   0.8728
   2.250   0.4556   0.00572   0.00157  -0.0542   0.5766   0.8851
   2.500   0.4778   0.00603   0.00170  -0.0530   0.5214   0.8973
   2.750   0.4961   0.00658   0.00190  -0.0511   0.4266   0.9110
   3.000   0.5152   0.00710   0.00212  -0.0494   0.3447   0.9265
   3.250   0.5348   0.00759   0.00234  -0.0477   0.2754   0.9432
   3.500   0.5557   0.00807   0.00257  -0.0463   0.2069   0.9587
   3.750   0.5814   0.00846   0.00278  -0.0460   0.1690   0.9710
   4.000   0.6111   0.00885   0.00299  -0.0467   0.1284   0.9799
   4.250   0.6425   0.00923   0.00322  -0.0477   0.0991   0.9871
   4.500   0.6751   0.00958   0.00346  -0.0490   0.0769   0.9926
   4.750   0.7089   0.00994   0.00370  -0.0505   0.0605   0.9958
   5.000   0.7434   0.01023   0.00394  -0.0522   0.0558   0.9988
   5.250   0.7682   0.01050   0.00419  -0.0517   0.0524   1.0000
   5.500   0.7881   0.01071   0.00441  -0.0501   0.0509   1.0000
   5.750   0.8097   0.01092   0.00463  -0.0489   0.0498   1.0000
   6.000   0.8320   0.01116   0.00488  -0.0478   0.0487   1.0000
   6.250   0.8548   0.01142   0.00516  -0.0469   0.0476   1.0000
   6.500   0.8776   0.01172   0.00546  -0.0460   0.0461   1.0000
   6.750   0.9000   0.01208   0.00582  -0.0450   0.0443   1.0000
   7.000   0.9203   0.01263   0.00642  -0.0436   0.0423   1.0000
   7.250   0.9440   0.01290   0.00671  -0.0429   0.0417   1.0000
   7.500   0.9680   0.01315   0.00698  -0.0423   0.0410   1.0000
   7.750   0.9920   0.01340   0.00725  -0.0417   0.0399   1.0000
   8.000   1.0157   0.01367   0.00753  -0.0410   0.0386   1.0000
   8.250   1.0388   0.01398   0.00785  -0.0403   0.0374   1.0000
   8.500   1.0611   0.01436   0.00823  -0.0394   0.0362   1.0000
   8.750   1.0778   0.01521   0.00914  -0.0376   0.0342   1.0000
   9.000   1.1032   0.01530   0.00924  -0.0373   0.0337   1.0000
   9.250   1.1277   0.01546   0.00942  -0.0368   0.0327   1.0000
   9.500   1.1514   0.01567   0.00966  -0.0362   0.0315   1.0000
   9.750   1.1748   0.01590   0.00989  -0.0355   0.0302   1.0000
  10.000   1.1959   0.01629   0.01026  -0.0345   0.0287   1.0000
  10.250   1.2160   0.01668   0.01069  -0.0333   0.0275   1.0000
  10.500   1.2383   0.01689   0.01092  -0.0325   0.0262   1.0000
  10.750   1.2601   0.01713   0.01116  -0.0316   0.0248   1.0000
  11.000   1.2787   0.01761   0.01162  -0.0301   0.0229   1.0000
  11.250   1.2994   0.01792   0.01197  -0.0291   0.0217   1.0000
  11.500   1.3189   0.01832   0.01238  -0.0279   0.0202   1.0000
  11.750   1.3351   0.01897   0.01303  -0.0262   0.0186   1.0000
  12.000   1.3532   0.01947   0.01359  -0.0248   0.0178   1.0000
  12.250   1.3702   0.02004   0.01420  -0.0233   0.0168   1.0000
  12.500   1.3852   0.02076   0.01494  -0.0215   0.0158   1.0000
  12.750   1.3976   0.02165   0.01589  -0.0194   0.0150   1.0000
  13.000   1.4128   0.02233   0.01665  -0.0178   0.0145   1.0000
  13.250   1.4270   0.02307   0.01747  -0.0161   0.0139   1.0000
  13.500   1.4403   0.02388   0.01833  -0.0143   0.0133   1.0000
  13.750   1.4512   0.02487   0.01937  -0.0124   0.0128   1.0000
  14.000   1.4563   0.02629   0.02087  -0.0098   0.0122   1.0000
  14.250   1.4660   0.02738   0.02206  -0.0079   0.0119   1.0000
  14.500   1.4763   0.02844   0.02321  -0.0061   0.0117   1.0000
  14.750   1.4853   0.02962   0.02449  -0.0044   0.0114   1.0000
  15.000   1.4929   0.03092   0.02589  -0.0026   0.0112   1.0000
  15.250   1.4994   0.03234   0.02740  -0.0009   0.0109   1.0000
  15.500   1.5049   0.03389   0.02904   0.0007   0.0107   1.0000
  15.750   1.5089   0.03561   0.03085   0.0023   0.0105   1.0000
  16.000   1.5107   0.03758   0.03292   0.0038   0.0103   1.0000
  16.250   1.5098   0.03989   0.03533   0.0051   0.0101   1.0000
  16.500   1.5049   0.04270   0.03826   0.0063   0.0099   1.0000
  16.750   1.4956   0.04615   0.04185   0.0071   0.0097   1.0000
  17.000   1.4816   0.05043   0.04628   0.0073   0.0096   1.0000
  17.250   1.4693   0.05485   0.05085   0.0068   0.0095   1.0000
  17.500   1.4632   0.05877   0.05491   0.0060   0.0094   1.0000
  17.750   1.4540   0.06339   0.05966   0.0046   0.0094   1.0000
  18.000   1.4407   0.06884   0.06527   0.0026   0.0093   1.0000
  18.250   1.4239   0.07519   0.07177  -0.0002   0.0093   1.0000
  18.500   1.4020   0.08278   0.07952  -0.0039   0.0093   1.0000
  18.750   1.3745   0.09176   0.08868  -0.0086   0.0093   1.0000
  19.000   1.3396   0.10247   0.09957  -0.0143   0.0093   1.0000
<< Back to LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il)

Polar data table (+)

Polar graphs


<< Back to LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il)