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RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il)
Reynolds number: 100,000
Max Cl/Cd: 42.69 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-rae5213-il-100000.txt
Download as CSV file: xf-rae5213-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4882   0.09540   0.09014  -0.0202   1.0000   0.1276
  -8.750  -0.4975   0.09182   0.08664  -0.0233   1.0000   0.1341
  -8.500  -0.5533   0.08623   0.08122  -0.0349   1.0000   0.1363
  -8.250  -0.4066   0.07560   0.07086  -0.0255   1.0000   0.1567
  -8.000  -0.4051   0.07248   0.06778  -0.0254   1.0000   0.1655
  -7.500  -0.5132   0.07358   0.06876  -0.0280   1.0000   0.1617
  -7.250  -0.5587   0.06717   0.06221  -0.0376   1.0000   0.1706
  -7.000  -0.5257   0.06576   0.06101  -0.0316   1.0000   0.1796
  -6.750  -0.5300   0.06223   0.05750  -0.0321   1.0000   0.1920
  -6.500  -0.5316   0.05921   0.05449  -0.0319   1.0000   0.2077
  -6.250  -0.5262   0.05692   0.05225  -0.0301   1.0000   0.2254
  -6.000  -0.5243   0.03921   0.03207  -0.0410   1.0000   0.0948
  -5.750  -0.5045   0.03481   0.02709  -0.0396   1.0000   0.0801
  -5.500  -0.4858   0.03169   0.02371  -0.0385   1.0000   0.0768
  -5.250  -0.4655   0.02910   0.02069  -0.0372   1.0000   0.0750
  -5.000  -0.4449   0.02735   0.01868  -0.0361   1.0000   0.0769
  -4.750  -0.4232   0.02562   0.01668  -0.0348   1.0000   0.0779
  -4.500  -0.4010   0.02403   0.01486  -0.0336   1.0000   0.0787
  -4.250  -0.3787   0.02305   0.01359  -0.0323   1.0000   0.0816
  -4.000  -0.3572   0.02147   0.01213  -0.0313   1.0000   0.0851
  -3.750  -0.3353   0.02048   0.01114  -0.0301   1.0000   0.0886
  -3.500  -0.3135   0.01973   0.01032  -0.0289   1.0000   0.0939
  -3.250  -0.2923   0.01870   0.00951  -0.0279   1.0000   0.0998
  -3.000  -0.2708   0.01801   0.00884  -0.0268   1.0000   0.1075
  -2.750  -0.2493   0.01724   0.00822  -0.0260   1.0000   0.1230
  -2.500  -0.2258   0.01590   0.00734  -0.0259   1.0000   0.1822
  -2.250  -0.2161   0.01486   0.00838  -0.0218   1.0000   0.6535
  -2.000  -0.2026   0.01533   0.00887  -0.0183   1.0000   0.6962
  -1.750  -0.1913   0.01572   0.00932  -0.0143   1.0000   0.7325
  -1.500  -0.1834   0.01602   0.00972  -0.0095   1.0000   0.7688
  -1.250  -0.1792   0.01618   0.00999  -0.0039   1.0000   0.8056
  -1.000  -0.1752   0.01619   0.01007   0.0015   1.0000   0.8386
  -0.750  -0.1528   0.01634   0.01023   0.0032   0.9925   0.8693
  -0.500  -0.1151   0.01655   0.01036   0.0010   0.9840   0.8850
  -0.250  -0.0752   0.01673   0.01045  -0.0019   0.9752   0.8967
   0.000  -0.0370   0.01683   0.01052  -0.0045   0.9659   0.9079
   0.250   0.0031   0.01697   0.01061  -0.0073   0.9567   0.9201
   0.500   0.0515   0.01718   0.01082  -0.0117   0.9489   0.9320
   0.750   0.0942   0.01727   0.01091  -0.0151   0.9385   0.9451
   1.000   0.1484   0.01742   0.01109  -0.0206   0.9295   0.9568
   1.250   0.2160   0.01734   0.01105  -0.0278   0.9174   0.9640
   1.500   0.2900   0.01641   0.01014  -0.0340   0.8910   0.9652
   1.750   0.3572   0.01531   0.00909  -0.0387   0.8686   0.9673
   2.000   0.4083   0.01472   0.00856  -0.0418   0.8498   0.9749
   2.250   0.4550   0.01417   0.00808  -0.0442   0.8270   0.9844
   2.500   0.4989   0.01363   0.00758  -0.0461   0.7969   0.9955
   2.750   0.5197   0.01332   0.00727  -0.0441   0.7633   1.0000
   3.000   0.5358   0.01310   0.00697  -0.0413   0.7232   1.0000
   3.250   0.5541   0.01298   0.00669  -0.0387   0.6524   1.0000
   3.500   0.5637   0.01395   0.00632  -0.0343   0.3993   1.0000
   3.750   0.5766   0.01593   0.00708  -0.0326   0.2507   1.0000
   4.000   0.6002   0.01700   0.00779  -0.0323   0.2177   1.0000
   4.250   0.6254   0.01796   0.00852  -0.0321   0.1983   1.0000
   4.500   0.6518   0.01890   0.00930  -0.0321   0.1837   1.0000
   4.750   0.6789   0.01993   0.01020  -0.0321   0.1720   1.0000
   5.000   0.7062   0.02118   0.01123  -0.0322   0.1616   1.0000
   5.250   0.7336   0.02209   0.01221  -0.0321   0.1519   1.0000
   5.500   0.7610   0.02345   0.01347  -0.0321   0.1432   1.0000
   5.750   0.7875   0.02450   0.01455  -0.0319   0.1346   1.0000
   6.000   0.8140   0.02603   0.01612  -0.0318   0.1272   1.0000
   6.250   0.8397   0.02722   0.01738  -0.0315   0.1199   1.0000
   6.500   0.8648   0.02905   0.01929  -0.0312   0.1140   1.0000
   6.750   0.8890   0.03054   0.02103  -0.0306   0.1082   1.0000
   7.000   0.9138   0.03250   0.02291  -0.0305   0.1036   1.0000
   7.250   0.9337   0.03464   0.02554  -0.0293   0.0997   1.0000
   7.500   0.9534   0.03693   0.02822  -0.0282   0.0965   1.0000
   7.750   0.9724   0.03944   0.03102  -0.0272   0.0944   1.0000
   8.000   0.9936   0.04170   0.03332  -0.0268   0.0921   1.0000
   8.250   1.0096   0.04551   0.03724  -0.0262   0.0902   1.0000
   8.500   1.0178   0.04872   0.04104  -0.0243   0.0894   1.0000
   8.750   1.0256   0.05274   0.04546  -0.0228   0.0894   1.0000
   9.000   1.0343   0.05730   0.05025  -0.0219   0.0900   1.0000
   9.250   0.9884   0.06685   0.06097  -0.0185   0.1002   1.0000
   9.500   0.9027   0.09650   0.09144  -0.0267   0.1785   1.0000
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