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LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-5A BL758.6 AIRFOIL (c5d-il)
Reynolds number: 50,000
Max Cl/Cd: 30.75 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c5d-il-50000.txt
Download as CSV file: xf-c5d-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4589   0.10823   0.10064  -0.0177   1.0000   0.3087
  -8.750  -0.4622   0.10569   0.09818  -0.0166   1.0000   0.3230
  -8.500  -0.4616   0.10301   0.09555  -0.0151   1.0000   0.3386
  -8.250  -0.4590   0.10021   0.09281  -0.0135   1.0000   0.3546
  -7.750  -0.4506   0.09449   0.08719  -0.0099   1.0000   0.3877
  -7.250  -0.4452   0.08951   0.08232  -0.0051   1.0000   0.4292
  -6.500  -0.6317   0.06055   0.05270  -0.0285   1.0000   0.1603
  -6.250  -0.6296   0.05513   0.04680  -0.0277   1.0000   0.1484
  -6.000  -0.6180   0.05145   0.04282  -0.0265   1.0000   0.1439
  -5.750  -0.6057   0.04771   0.03877  -0.0253   1.0000   0.1402
  -5.500  -0.5918   0.04389   0.03436  -0.0241   1.0000   0.1360
  -5.250  -0.5746   0.04100   0.03105  -0.0229   1.0000   0.1366
  -5.000  -0.5556   0.03858   0.02827  -0.0218   1.0000   0.1402
  -4.750  -0.5343   0.03617   0.02538  -0.0208   1.0000   0.1433
  -4.500  -0.5109   0.03403   0.02263  -0.0197   1.0000   0.1467
  -4.250  -0.4880   0.03209   0.02077  -0.0190   1.0000   0.1559
  -4.000  -0.4628   0.03028   0.01865  -0.0182   1.0000   0.1648
  -3.750  -0.4373   0.02877   0.01704  -0.0175   1.0000   0.1793
  -3.500  -0.4113   0.02729   0.01566  -0.0168   1.0000   0.1988
  -3.250  -0.3853   0.02587   0.01441  -0.0160   1.0000   0.2320
  -3.000  -0.3599   0.02387   0.01291  -0.0152   1.0000   0.3058
  -2.750  -0.3563   0.02100   0.01293  -0.0075   1.0000   0.7107
  -2.500  -0.1367   0.02405   0.01481  -0.0318   1.0000   1.0000
  -2.250  -0.1363   0.02362   0.01426  -0.0285   1.0000   1.0000
  -2.000  -0.1361   0.02322   0.01374  -0.0251   1.0000   1.0000
  -1.750  -0.1359   0.02286   0.01328  -0.0216   1.0000   1.0000
  -1.500  -0.1354   0.02254   0.01285  -0.0181   1.0000   1.0000
  -1.250  -0.1339   0.02225   0.01247  -0.0147   1.0000   1.0000
  -1.000  -0.1304   0.02204   0.01214  -0.0115   1.0000   1.0000
  -0.750  -0.1239   0.02192   0.01188  -0.0088   1.0000   1.0000
  -0.500  -0.1133   0.02190   0.01171  -0.0068   1.0000   1.0000
  -0.250  -0.0993   0.02197   0.01165  -0.0053   1.0000   1.0000
   0.000  -0.0833   0.02213   0.01168  -0.0042   1.0000   1.0000
   0.250  -0.0659   0.02235   0.01179  -0.0033   1.0000   1.0000
   0.500  -0.0476   0.02263   0.01196  -0.0026   1.0000   1.0000
   0.750  -0.0288   0.02297   0.01220  -0.0020   1.0000   1.0000
   1.000  -0.0097   0.02335   0.01251  -0.0016   1.0000   1.0000
   1.250   0.0096   0.02378   0.01288  -0.0012   1.0000   1.0000
   1.500   0.0290   0.02426   0.01331  -0.0008   1.0000   1.0000
   1.750   0.0484   0.02478   0.01381  -0.0006   1.0000   1.0000
   2.000   0.0677   0.02536   0.01437  -0.0003   1.0000   1.0000
   2.250   0.0869   0.02599   0.01499  -0.0002   1.0000   1.0000
   2.500   0.1058   0.02667   0.01567  -0.0001   1.0000   1.0000
   2.750   0.1246   0.02740   0.01643   0.0000   1.0000   1.0000
   3.000   0.1430   0.02820   0.01726   0.0000   1.0000   1.0000
   3.250   0.1611   0.02906   0.01817   0.0000   1.0000   1.0000
   3.500   0.1788   0.02999   0.01915  -0.0001   1.0000   1.0000
   3.750   0.2040   0.03117   0.02042  -0.0018   0.9965   1.0000
   4.000   0.2726   0.03316   0.02262  -0.0114   0.9703   1.0000
   4.250   0.3353   0.03452   0.02421  -0.0190   0.9396   1.0000
   4.500   0.4146   0.03518   0.02519  -0.0279   0.9031   1.0000
   4.750   0.4743   0.03475   0.02508  -0.0322   0.8638   1.0000
   5.000   0.5481   0.03290   0.02366  -0.0363   0.8211   1.0000
   5.250   0.6229   0.02948   0.02078  -0.0382   0.7764   1.0000
   5.500   0.6962   0.02366   0.01541  -0.0351   0.6871   1.0000
   5.750   0.7213   0.02346   0.01324  -0.0277   0.3862   1.0000
   6.000   0.7346   0.02605   0.01473  -0.0250   0.2868   1.0000
   6.250   0.7720   0.02825   0.01652  -0.0262   0.2391   1.0000
   6.500   0.8109   0.03025   0.01827  -0.0278   0.2140   1.0000
   6.750   0.8444   0.03215   0.02017  -0.0285   0.1981   1.0000
   7.000   0.8764   0.03422   0.02235  -0.0289   0.1883   1.0000
   7.250   0.9028   0.03644   0.02486  -0.0285   0.1806   1.0000
   7.500   0.9277   0.03859   0.02713  -0.0279   0.1727   1.0000
   7.750   0.9510   0.04142   0.03020  -0.0272   0.1687   1.0000
   8.000   0.9658   0.04399   0.03333  -0.0250   0.1653   1.0000
   8.250   0.9794   0.04664   0.03637  -0.0230   0.1608   1.0000
   8.500   0.9940   0.04963   0.03967  -0.0212   0.1579   1.0000
   8.750   1.0141   0.05349   0.04352  -0.0207   0.1547   1.0000
   9.000   1.0134   0.05679   0.04742  -0.0172   0.1536   1.0000
   9.250   1.0109   0.06054   0.05165  -0.0141   0.1530   1.0000
   9.500   1.0103   0.06485   0.05630  -0.0116   0.1536   1.0000
   9.750   1.0092   0.06945   0.06116  -0.0095   0.1542   1.0000
  10.000   0.9482   0.07511   0.06753  -0.0042   0.1633   1.0000
  10.250   0.9298   0.08028   0.07283  -0.0025   0.1669   1.0000
  10.500   0.9313   0.08576   0.07835  -0.0021   0.1693   1.0000
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