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RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il)
Reynolds number: 50,000
Max Cl/Cd: 29.59 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5213-il-50000.txt
Download as CSV file: xf-rae5213-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: RAE(NPL) 5213 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4342   0.10209   0.09475  -0.0002   1.0000   0.3501
  -8.250  -0.4286   0.09914   0.09185   0.0003   1.0000   0.3657
  -7.750  -0.4147   0.09326   0.08608   0.0018   1.0000   0.3996
  -7.500  -0.4058   0.09031   0.08318   0.0027   1.0000   0.4174
  -7.250  -0.3981   0.08742   0.08033   0.0035   1.0000   0.4345
  -7.000  -0.3962   0.08484   0.07783   0.0044   1.0000   0.4494
  -6.750  -0.3886   0.08137   0.07441   0.0044   1.0000   0.4528
  -6.500  -0.5438   0.05657   0.04934  -0.0378   1.0000   0.1740
  -6.250  -0.5375   0.05036   0.04239  -0.0407   1.0000   0.1500
  -6.000  -0.5247   0.04585   0.03694  -0.0415   1.0000   0.1363
  -5.750  -0.5069   0.04214   0.03316  -0.0408   1.0000   0.1334
  -5.500  -0.4886   0.03908   0.02972  -0.0402   1.0000   0.1324
  -5.250  -0.4685   0.03637   0.02661  -0.0394   1.0000   0.1326
  -5.000  -0.4469   0.03387   0.02374  -0.0386   1.0000   0.1326
  -4.750  -0.4242   0.03174   0.02123  -0.0376   1.0000   0.1340
  -4.500  -0.4013   0.02984   0.01900  -0.0365   1.0000   0.1377
  -4.250  -0.3789   0.02796   0.01714  -0.0353   1.0000   0.1422
  -4.000  -0.3558   0.02652   0.01559  -0.0338   1.0000   0.1482
  -3.750  -0.3338   0.02514   0.01424  -0.0321   1.0000   0.1572
  -3.500  -0.3121   0.02405   0.01309  -0.0302   1.0000   0.1689
  -3.250  -0.2922   0.02277   0.01203  -0.0285   1.0000   0.1878
  -3.000  -0.2717   0.02120   0.01084  -0.0274   1.0000   0.2264
  -2.750  -0.2703   0.01936   0.01158  -0.0203   1.0000   0.6400
  -2.500  -0.2796   0.02038   0.01274  -0.0086   1.0000   0.7395
  -2.250  -0.2846   0.02064   0.01302   0.0009   1.0000   0.7973
  -2.000  -0.0777   0.02180   0.01328  -0.0154   1.0000   0.9805
  -1.750  -0.0214   0.02112   0.01235  -0.0225   1.0000   0.9964
  -1.500  -0.0100   0.02083   0.01201  -0.0218   1.0000   1.0000
  -1.250  -0.0147   0.02067   0.01184  -0.0183   1.0000   1.0000
  -1.000  -0.0214   0.02050   0.01168  -0.0145   1.0000   1.0000
  -0.750  -0.0295   0.02031   0.01149  -0.0107   1.0000   1.0000
  -0.500  -0.0389   0.02006   0.01126  -0.0067   1.0000   1.0000
  -0.250  -0.0478   0.01977   0.01096  -0.0029   1.0000   1.0000
   0.000  -0.0504   0.01953   0.01069  -0.0002   1.0000   1.0000
   0.250  -0.0391   0.01950   0.01058   0.0004   1.0000   1.0000
   0.500  -0.0201   0.01964   0.01063  -0.0003   1.0000   1.0000
   0.750   0.0023   0.01990   0.01081  -0.0014   1.0000   1.0000
   1.000   0.0259   0.02026   0.01109  -0.0027   1.0000   1.0000
   1.250   0.0498   0.02070   0.01147  -0.0039   1.0000   1.0000
   1.500   0.0733   0.02121   0.01193  -0.0051   1.0000   1.0000
   1.750   0.0962   0.02179   0.01248  -0.0063   1.0000   1.0000
   2.000   0.1185   0.02245   0.01312  -0.0073   1.0000   1.0000
   2.250   0.1399   0.02318   0.01385  -0.0082   1.0000   1.0000
   2.500   0.1736   0.02428   0.01498  -0.0115   0.9939   1.0000
   2.750   0.2602   0.02601   0.01689  -0.0235   0.9558   1.0000
   3.000   0.3994   0.02545   0.01676  -0.0386   0.8782   1.0000
   3.250   0.4766   0.02426   0.01594  -0.0435   0.8373   1.0000
   3.500   0.5413   0.02219   0.01423  -0.0441   0.7880   1.0000
   3.750   0.5818   0.01984   0.01202  -0.0390   0.6984   1.0000
   4.000   0.5939   0.02007   0.01046  -0.0302   0.4208   1.0000
   4.250   0.6136   0.02213   0.01151  -0.0287   0.3331   1.0000
   4.500   0.6420   0.02369   0.01271  -0.0286   0.2929   1.0000
   4.750   0.6722   0.02517   0.01396  -0.0287   0.2667   1.0000
   5.000   0.7029   0.02678   0.01535  -0.0289   0.2472   1.0000
   5.250   0.7320   0.02838   0.01696  -0.0289   0.2312   1.0000
   5.500   0.7599   0.03013   0.01885  -0.0288   0.2183   1.0000
   5.750   0.7866   0.03211   0.02090  -0.0286   0.2071   1.0000
   6.000   0.8128   0.03412   0.02295  -0.0283   0.1970   1.0000
   6.250   0.8354   0.03644   0.02567  -0.0276   0.1888   1.0000
   6.500   0.8597   0.03872   0.02796  -0.0272   0.1805   1.0000
   6.750   0.8784   0.04164   0.03132  -0.0263   0.1753   1.0000
   7.000   0.8945   0.04461   0.03479  -0.0252   0.1705   1.0000
   7.250   0.9105   0.04783   0.03835  -0.0243   0.1673   1.0000
   7.500   0.9302   0.05111   0.04165  -0.0239   0.1634   1.0000
   7.750   0.9415   0.05526   0.04610  -0.0231   0.1617   1.0000
   8.000   0.9505   0.05974   0.05092  -0.0223   0.1621   1.0000
   8.250   0.9182   0.06678   0.05900  -0.0215   0.1717   1.0000
   8.500   0.9163   0.07244   0.06483  -0.0217   0.1761   1.0000
   8.750   0.6805   0.10991   0.10249  -0.0625   0.4068   1.0000
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