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CAP 21 (TraCFoil) (cap21c-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: CAP 21 (TraCFoil) (cap21c-il)
Reynolds number: 50,000
Max Cl/Cd: 14.64 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-cap21c-il-50000-n5.txt
Download as CSV file: xf-cap21c-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: CAP 21   (TraCFoil)                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5617   0.10858   0.09970   0.0118   1.0005   0.1661
  -9.750  -0.5702   0.10327   0.09437   0.0084   1.0005   0.1686
  -9.500  -0.5864   0.09694   0.08802   0.0035   1.0005   0.1713
  -9.250  -0.6074   0.08957   0.08067  -0.0022   1.0005   0.1741
  -9.000  -0.5943   0.08707   0.07821  -0.0010   1.0005   0.1764
  -8.750  -0.5745   0.08623   0.07743   0.0009   1.0005   0.1793
  -8.500  -0.5512   0.08589   0.07715   0.0030   1.0005   0.1827
  -8.250  -0.5341   0.08470   0.07602   0.0040   1.0005   0.1868
  -8.000  -0.5259   0.08229   0.07364   0.0035   1.0005   0.1910
  -7.750  -0.5261   0.07863   0.07001   0.0017   1.0005   0.1946
  -7.500  -0.5352   0.07365   0.06506  -0.0016   1.0005   0.1976
  -7.250  -0.5493   0.06758   0.05894  -0.0063   1.0005   0.2012
  -7.000  -0.5607   0.06183   0.05306  -0.0100   1.0005   0.2051
  -6.750  -0.5663   0.05701   0.04807  -0.0124   1.0005   0.2090
  -6.500  -0.5645   0.05348   0.04433  -0.0135   1.0005   0.2129
  -6.250  -0.5555   0.05144   0.04206  -0.0137   1.0005   0.2169
  -6.000  -0.5481   0.04842   0.03894  -0.0136   1.0005   0.2207
  -5.750  -0.5358   0.04565   0.03620  -0.0128   1.0005   0.2247
  -5.500  -0.5199   0.04391   0.03451  -0.0118   1.0005   0.2278
  -5.250  -0.5038   0.04227   0.03288  -0.0109   1.0005   0.2304
  -5.000  -0.4872   0.04073   0.03134  -0.0100   1.0005   0.2330
  -4.750  -0.4702   0.03927   0.02987  -0.0091   1.0005   0.2357
  -4.500  -0.4526   0.03787   0.02847  -0.0083   1.0005   0.2385
  -4.250  -0.4343   0.03653   0.02713  -0.0075   1.0005   0.2414
  -4.000  -0.3817   0.03494   0.02546  -0.0130   0.9368   0.2466
  -3.750  -0.3205   0.03401   0.02365  -0.0179   0.6332   0.2548
  -3.500  -0.3022   0.03393   0.02256  -0.0160   0.4955   0.2593
  -3.250  -0.2802   0.03346   0.02152  -0.0153   0.4474   0.2630
  -3.000  -0.2560   0.03284   0.02051  -0.0150   0.4221   0.2657
  -2.750  -0.2307   0.03225   0.01960  -0.0147   0.4058   0.2681
  -2.500  -0.2049   0.03178   0.01883  -0.0145   0.3933   0.2704
  -2.250  -0.1779   0.03135   0.01818  -0.0143   0.3829   0.2724
  -2.000  -0.1507   0.03101   0.01761  -0.0141   0.3738   0.2741
  -1.750  -0.1239   0.03031   0.01678  -0.0139   0.3667   0.2773
  -1.500  -0.0960   0.02980   0.01625  -0.0138   0.3602   0.2807
  -1.250  -0.0677   0.02946   0.01594  -0.0136   0.3538   0.2841
  -1.000  -0.0391   0.02924   0.01571  -0.0135   0.3477   0.2878
  -0.750  -0.0102   0.02914   0.01559  -0.0134   0.3423   0.2929
  -0.500   0.0187   0.02914   0.01553  -0.0133   0.3374   0.2993
  -0.250   0.0478   0.02926   0.01551  -0.0132   0.3325   0.3059
   0.000   0.0768   0.02923   0.01551  -0.0132   0.3271   0.3117
   0.250   0.1058   0.02926   0.01552  -0.0131   0.3205   0.3162
   0.500   0.1342   0.02924   0.01556  -0.0129   0.3139   0.3202
   0.750   0.1623   0.02930   0.01569  -0.0126   0.3085   0.3251
   1.000   0.1904   0.02949   0.01592  -0.0124   0.3044   0.3309
   1.250   0.2182   0.02975   0.01619  -0.0121   0.3006   0.3375
   1.500   0.2458   0.03015   0.01657  -0.0118   0.2970   0.3447
   1.750   0.2725   0.03069   0.01718  -0.0115   0.2934   0.3521
   2.000   0.2986   0.03136   0.01798  -0.0112   0.2905   0.3613
   2.250   0.3250   0.03176   0.01858  -0.0109   0.2884   0.3727
   2.500   0.3503   0.03220   0.01931  -0.0105   0.2860   0.3869
   2.750   0.3750   0.03272   0.02016  -0.0101   0.2832   0.4067
   3.000   0.3984   0.03318   0.02107  -0.0095   0.2795   0.4392
   3.250   0.4189   0.03343   0.02200  -0.0084   0.2748   0.5164
   3.500   0.4396   0.03325   0.02311  -0.0059   0.2692   0.7875
   3.750   0.4916   0.03423   0.02427  -0.0104   0.2616   0.9995
   4.000   0.5121   0.03537   0.02537  -0.0096   0.2578   0.9995
   4.250   0.5323   0.03656   0.02654  -0.0088   0.2543   0.9995
   4.500   0.5523   0.03779   0.02775  -0.0080   0.2510   0.9995
   4.750   0.5719   0.03907   0.02900  -0.0072   0.2479   0.9995
   5.000   0.5914   0.04044   0.03034  -0.0064   0.2448   0.9995
   5.250   0.6103   0.04200   0.03186  -0.0057   0.2417   0.9995
   5.500   0.6264   0.04426   0.03408  -0.0049   0.2378   0.9995
   5.750   0.6367   0.04722   0.03718  -0.0045   0.2338   0.9995
   6.000   0.6506   0.04864   0.03876  -0.0040   0.2303   0.9995
   6.250   0.6594   0.05083   0.04115  -0.0039   0.2255   0.9995
   6.500   0.6625   0.05403   0.04454  -0.0042   0.2208   0.9995
   6.750   0.6588   0.05822   0.04891  -0.0052   0.2165   0.9995
   7.000   0.6490   0.06319   0.05403  -0.0071   0.2122   0.9995
   7.250   0.6349   0.06868   0.05962  -0.0098   0.2082   0.9995
   7.500   0.6211   0.07441   0.06538  -0.0134   0.2046   0.9995
   7.750   0.6181   0.07880   0.06975  -0.0158   0.2015   0.9995
   8.000   0.6210   0.08231   0.07324  -0.0170   0.1990   0.9995
   8.250   0.6320   0.08456   0.07545  -0.0169   0.1963   0.9995
   8.500   0.6475   0.08599   0.07683  -0.0160   0.1935   0.9995
   8.750   0.6667   0.08681   0.07758  -0.0142   0.1907   0.9995
   9.000   0.6845   0.08815   0.07885  -0.0120   0.1879   0.9995
   9.250   0.6443   0.09797   0.08871  -0.0206   0.1822   0.9995
   9.500   0.6295   0.10420   0.09496  -0.0246   0.1790   0.9995
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