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LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL488.2 AIRFOIL (c5b-il)
Reynolds number: 50,000
Max Cl/Cd: 30.42 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5b-il-50000.txt
Download as CSV file: xf-c5b-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL488.2 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4797   0.10023   0.09290  -0.0104   1.0000   0.3880
  -8.000  -0.4594   0.09575   0.08841  -0.0097   1.0000   0.3956
  -7.500  -0.6778   0.06991   0.06264  -0.0305   1.0000   0.1676
  -7.250  -0.6889   0.06385   0.05625  -0.0296   1.0000   0.1518
  -7.000  -0.7010   0.05823   0.04992  -0.0278   1.0000   0.1393
  -6.750  -0.6909   0.05431   0.04589  -0.0264   1.0000   0.1358
  -6.500  -0.6844   0.05024   0.04140  -0.0246   1.0000   0.1315
  -6.250  -0.6761   0.04630   0.03674  -0.0227   1.0000   0.1276
  -6.000  -0.6612   0.04341   0.03351  -0.0212   1.0000   0.1286
  -5.750  -0.6442   0.04088   0.03069  -0.0199   1.0000   0.1309
  -5.500  -0.6252   0.03839   0.02782  -0.0186   1.0000   0.1331
  -5.250  -0.6038   0.03601   0.02502  -0.0173   1.0000   0.1351
  -5.000  -0.5813   0.03406   0.02253  -0.0161   1.0000   0.1397
  -4.750  -0.5580   0.03214   0.02064  -0.0154   1.0000   0.1480
  -4.500  -0.5325   0.03041   0.01865  -0.0144   1.0000   0.1566
  -4.250  -0.5069   0.02888   0.01713  -0.0136   1.0000   0.1718
  -4.000  -0.4812   0.02733   0.01576  -0.0127   1.0000   0.1948
  -3.750  -0.4567   0.02556   0.01433  -0.0116   1.0000   0.2442
  -3.500  -0.4483   0.02177   0.01323  -0.0072   1.0000   0.5461
  -3.250  -0.4494   0.02234   0.01451   0.0042   1.0000   0.7728
  -3.000  -0.3278   0.02653   0.01797  -0.0003   1.0000   0.9366
  -2.750  -0.1212   0.02672   0.01696  -0.0340   1.0000   1.0000
  -2.500  -0.1200   0.02614   0.01628  -0.0313   1.0000   1.0000
  -2.250  -0.1188   0.02563   0.01568  -0.0284   1.0000   1.0000
  -2.000  -0.1177   0.02517   0.01513  -0.0253   1.0000   1.0000
  -1.750  -0.1169   0.02475   0.01464  -0.0221   1.0000   1.0000
  -1.500  -0.1162   0.02436   0.01418  -0.0188   1.0000   1.0000
  -1.250  -0.1157   0.02400   0.01375  -0.0154   1.0000   1.0000
  -1.000  -0.1151   0.02366   0.01336  -0.0119   1.0000   1.0000
  -0.750  -0.1139   0.02337   0.01299  -0.0085   1.0000   1.0000
  -0.500  -0.1113   0.02313   0.01267  -0.0052   1.0000   1.0000
  -0.250  -0.1065   0.02297   0.01243  -0.0023   1.0000   1.0000
   0.000  -0.0979   0.02291   0.01228   0.0000   1.0000   1.0000
   0.250  -0.0855   0.02297   0.01224   0.0017   1.0000   1.0000
   0.500  -0.0705   0.02312   0.01229   0.0029   1.0000   1.0000
   0.750  -0.0539   0.02334   0.01244   0.0038   1.0000   1.0000
   1.000  -0.0363   0.02363   0.01266   0.0045   1.0000   1.0000
   1.250  -0.0180   0.02398   0.01295   0.0051   1.0000   1.0000
   1.500   0.0007   0.02438   0.01331   0.0056   1.0000   1.0000
   1.750   0.0196   0.02484   0.01374   0.0059   1.0000   1.0000
   2.000   0.0385   0.02534   0.01423   0.0063   1.0000   1.0000
   2.250   0.0574   0.02590   0.01479   0.0065   1.0000   1.0000
   2.500   0.0762   0.02652   0.01541   0.0067   1.0000   1.0000
   2.750   0.0949   0.02719   0.01611   0.0068   1.0000   1.0000
   3.000   0.1132   0.02792   0.01687   0.0069   1.0000   1.0000
   3.250   0.1313   0.02871   0.01772   0.0070   1.0000   1.0000
   3.500   0.1490   0.02958   0.01865   0.0069   1.0000   1.0000
   3.750   0.1663   0.03052   0.01966   0.0068   1.0000   1.0000
   4.000   0.1975   0.03190   0.02117   0.0039   0.9946   1.0000
   4.250   0.2693   0.03391   0.02343  -0.0062   0.9649   1.0000
   4.500   0.3379   0.03511   0.02492  -0.0146   0.9290   1.0000
   4.750   0.4222   0.03490   0.02509  -0.0231   0.8811   1.0000
   5.000   0.4982   0.03367   0.02430  -0.0288   0.8419   1.0000
   5.250   0.5597   0.03176   0.02284  -0.0311   0.8028   1.0000
   5.500   0.6454   0.02587   0.01760  -0.0309   0.7346   1.0000
   5.750   0.7008   0.02304   0.01330  -0.0253   0.4262   1.0000
   6.000   0.7109   0.02565   0.01461  -0.0218   0.3076   1.0000
   6.250   0.7504   0.02810   0.01647  -0.0235   0.2478   1.0000
   6.500   0.7901   0.03012   0.01827  -0.0252   0.2178   1.0000
   6.750   0.8254   0.03210   0.02031  -0.0262   0.2007   1.0000
   7.000   0.8594   0.03437   0.02254  -0.0272   0.1893   1.0000
   7.250   0.8833   0.03628   0.02476  -0.0263   0.1794   1.0000
   7.500   0.9088   0.03884   0.02752  -0.0258   0.1730   1.0000
   7.750   0.9270   0.04121   0.03036  -0.0240   0.1676   1.0000
   8.000   0.9516   0.04398   0.03307  -0.0238   0.1605   1.0000
   8.250   0.9619   0.04677   0.03643  -0.0210   0.1581   1.0000
   8.500   0.9691   0.04974   0.03994  -0.0180   0.1554   1.0000
   8.750   0.9750   0.05285   0.04348  -0.0152   0.1525   1.0000
   9.000   0.9777   0.05643   0.04749  -0.0123   0.1516   1.0000
   9.250   0.9738   0.06043   0.05192  -0.0091   0.1522   1.0000
   9.500   0.9649   0.06465   0.05651  -0.0059   0.1533   1.0000
   9.750   0.9520   0.06909   0.06126  -0.0029   0.1548   1.0000
  10.000   0.9374   0.07371   0.06610  -0.0004   0.1566   1.0000
  10.250   0.9257   0.07849   0.07102   0.0015   0.1584   1.0000
  10.500   0.8546   0.08596   0.07869   0.0031   0.1712   1.0000
  10.750   0.8547   0.09176   0.08456   0.0026   0.1761   1.0000
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