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LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)
Reynolds number: 50,000
Max Cl/Cd: 31.7 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5e-il-50000.txt
Download as CSV file: xf-c5e-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5143   0.10842   0.10094  -0.0065   1.0000   0.2693
  -8.500  -0.5017   0.10468   0.09724  -0.0053   1.0000   0.2857
  -8.250  -0.5014   0.10175   0.09437  -0.0047   1.0000   0.3028
  -8.000  -0.4645   0.09719   0.08975  -0.0014   1.0000   0.3268
  -7.750  -0.4736   0.09533   0.08800  -0.0005   1.0000   0.3517
  -7.500  -0.4477   0.09187   0.08454   0.0021   1.0000   0.3804
  -7.250  -0.4470   0.09019   0.08293   0.0047   1.0000   0.4161
  -7.000  -0.4115   0.08694   0.07965   0.0079   1.0000   0.4599
  -6.750  -0.3968   0.08535   0.07810   0.0118   1.0000   0.5132
  -6.500  -0.3657   0.08232   0.07507   0.0144   1.0000   0.5668
  -6.250  -0.3437   0.07980   0.07256   0.0166   1.0000   0.6156
  -6.000  -0.3257   0.07771   0.07050   0.0189   1.0000   0.6639
  -5.750  -0.2875   0.07345   0.06621   0.0182   1.0000   0.7129
  -5.500  -0.2664   0.06946   0.06225   0.0164   1.0000   0.7230
  -5.000  -0.5044   0.05044   0.04298  -0.0204   1.0000   0.3027
  -4.750  -0.4686   0.04564   0.03668  -0.0259   1.0000   0.2034
  -4.500  -0.4495   0.04226   0.03299  -0.0253   1.0000   0.1884
  -4.250  -0.4306   0.03981   0.03031  -0.0244   1.0000   0.1814
  -4.000  -0.4111   0.03755   0.02771  -0.0237   1.0000   0.1768
  -3.750  -0.3910   0.03572   0.02557  -0.0229   1.0000   0.1770
  -3.500  -0.3699   0.03405   0.02361  -0.0222   1.0000   0.1779
  -3.250  -0.3474   0.03246   0.02174  -0.0215   1.0000   0.1779
  -3.000  -0.3243   0.03105   0.02006  -0.0209   1.0000   0.1790
  -2.750  -0.3010   0.02998   0.01870  -0.0203   1.0000   0.1842
  -2.500  -0.2777   0.02872   0.01735  -0.0198   1.0000   0.1903
  -2.250  -0.2538   0.02768   0.01625  -0.0191   1.0000   0.1966
  -2.000  -0.2294   0.02678   0.01528  -0.0185   1.0000   0.2061
  -1.750  -0.2057   0.02604   0.01452  -0.0177   1.0000   0.2201
  -1.500  -0.1826   0.02523   0.01376  -0.0167   1.0000   0.2361
  -1.250  -0.1595   0.02418   0.01296  -0.0161   1.0000   0.2636
  -1.000  -0.1333   0.02269   0.01195  -0.0167   1.0000   0.3197
  -0.750  -0.1346   0.02095   0.01279  -0.0081   1.0000   0.8080
  -0.500  -0.0901   0.02143   0.01310  -0.0064   1.0000   1.0000
  -0.250  -0.0841   0.02149   0.01295  -0.0043   1.0000   1.0000
   0.000  -0.0717   0.02167   0.01292  -0.0033   1.0000   1.0000
   0.250  -0.0553   0.02196   0.01301  -0.0031   1.0000   1.0000
   0.500  -0.0366   0.02233   0.01321  -0.0032   1.0000   1.0000
   0.750  -0.0167   0.02278   0.01350  -0.0035   1.0000   1.0000
   1.000   0.0038   0.02329   0.01389  -0.0040   1.0000   1.0000
   1.250   0.0246   0.02387   0.01436  -0.0045   1.0000   1.0000
   1.500   0.0455   0.02451   0.01490  -0.0051   1.0000   1.0000
   1.750   0.0768   0.02537   0.01569  -0.0077   0.9956   1.0000
   2.000   0.1240   0.02653   0.01679  -0.0130   0.9844   1.0000
   2.250   0.1666   0.02762   0.01785  -0.0175   0.9730   1.0000
   2.500   0.2063   0.02867   0.01890  -0.0213   0.9611   1.0000
   2.750   0.2438   0.02971   0.01997  -0.0247   0.9490   1.0000
   3.000   0.2818   0.03079   0.02110  -0.0281   0.9366   1.0000
   3.250   0.3221   0.03189   0.02228  -0.0317   0.9232   1.0000
   3.500   0.3689   0.03270   0.02321  -0.0356   0.8998   1.0000
   3.750   0.4486   0.03248   0.02323  -0.0420   0.8593   1.0000
   4.000   0.5138   0.03145   0.02245  -0.0448   0.8196   1.0000
   4.250   0.5790   0.02965   0.02096  -0.0460   0.7849   1.0000
   4.500   0.6280   0.02779   0.01938  -0.0444   0.7517   1.0000
   4.750   0.6688   0.02500   0.01679  -0.0396   0.7031   1.0000
   5.000   0.6922   0.02229   0.01410  -0.0320   0.6208   1.0000
   5.250   0.6956   0.02194   0.01225  -0.0226   0.3852   1.0000
   5.500   0.7042   0.02434   0.01343  -0.0194   0.2878   1.0000
   5.750   0.7271   0.02629   0.01493  -0.0183   0.2475   1.0000
   6.000   0.7564   0.02811   0.01636  -0.0182   0.2224   1.0000
   6.250   0.7881   0.02987   0.01796  -0.0183   0.2065   1.0000
   6.500   0.8181   0.03158   0.01983  -0.0182   0.1960   1.0000
   6.750   0.8465   0.03357   0.02187  -0.0181   0.1872   1.0000
   7.000   0.8732   0.03553   0.02393  -0.0178   0.1796   1.0000
   7.250   0.9002   0.03812   0.02660  -0.0177   0.1754   1.0000
   7.500   0.9209   0.04044   0.02942  -0.0167   0.1720   1.0000
   7.750   0.9402   0.04292   0.03228  -0.0157   0.1676   1.0000
   8.000   0.9596   0.04564   0.03525  -0.0149   0.1644   1.0000
   8.250   0.9763   0.04883   0.03877  -0.0139   0.1632   1.0000
   8.500   0.9965   0.05257   0.04256  -0.0136   0.1608   1.0000
   8.750   1.0027   0.05611   0.04661  -0.0120   0.1600   1.0000
   9.000   1.0077   0.06012   0.05105  -0.0107   0.1599   1.0000
   9.250   0.9924   0.06492   0.05660  -0.0087   0.1640   1.0000
   9.500   0.9634   0.07136   0.06355  -0.0077   0.1698   1.0000
   9.750   0.9541   0.07701   0.06936  -0.0077   0.1736   1.0000
  10.000   0.9685   0.08238   0.07474  -0.0079   0.1760   1.0000
  10.250   0.8540   0.09908   0.09172  -0.0182   0.2066   1.0000
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