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EPPLER 327 AIRFOIL (e327-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 327 AIRFOIL (e327-il)
Reynolds number: 50,000
Max Cl/Cd: 17.78 at α=1.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e327-il-50000.txt
Download as CSV file: xf-e327-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 327 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4056   0.10708   0.10070  -0.0036   1.0000   0.2820
  -9.000  -0.4011   0.10408   0.09777  -0.0030   1.0000   0.2991
  -8.750  -0.4123   0.10187   0.09567  -0.0026   1.0000   0.3201
  -8.500  -0.3907   0.09793   0.09176  -0.0008   1.0000   0.3424
  -8.250  -0.4043   0.09636   0.09032   0.0005   1.0000   0.3687
  -8.000  -0.3948   0.09359   0.08762   0.0031   1.0000   0.4008
  -7.750  -0.3531   0.08925   0.08327   0.0056   1.0000   0.4396
  -7.500  -0.3340   0.08646   0.08053   0.0086   1.0000   0.4860
  -7.250  -0.3067   0.08363   0.07772   0.0112   1.0000   0.5381
  -6.250  -0.3598   0.06982   0.06449   0.0088   1.0000   0.4854
  -6.000  -0.4287   0.06534   0.06035   0.0075   1.0000   0.4380
  -5.750  -0.4815   0.06142   0.05664   0.0079   1.0000   0.4073
  -5.500  -0.5250   0.05838   0.05367   0.0092   1.0000   0.3761
  -5.250  -0.5650   0.05733   0.05262   0.0141   1.0000   0.3707
  -4.750  -0.5643   0.04959   0.04267   0.0102   1.0000   0.1576
  -4.500  -0.5571   0.04704   0.03968   0.0126   1.0000   0.1368
  -4.250  -0.5224   0.04463   0.03615   0.0119   0.9915   0.1142
  -4.000  -0.4708   0.04052   0.03171   0.0071   0.9762   0.1072
  -3.750  -0.4165   0.03763   0.02825   0.0027   0.9604   0.1074
  -3.500  -0.3584   0.03508   0.02520  -0.0020   0.9452   0.1083
  -3.250  -0.0227   0.02784   0.02079  -0.0334   0.9908   1.0000
  -3.000   0.0600   0.02705   0.01927  -0.0454   0.9615   1.0000
  -2.750   0.1382   0.02610   0.01777  -0.0561   0.9367   1.0000
  -2.500   0.2077   0.02521   0.01646  -0.0648   0.9130   1.0000
  -2.250   0.2551   0.02479   0.01570  -0.0690   0.8859   1.0000
  -2.000   0.2877   0.02472   0.01536  -0.0703   0.8611   1.0000
  -1.750   0.3123   0.02486   0.01528  -0.0700   0.8382   1.0000
  -1.500   0.3344   0.02508   0.01528  -0.0692   0.8186   1.0000
  -1.250   0.3542   0.02541   0.01545  -0.0681   0.8005   1.0000
  -1.000   0.3734   0.02578   0.01569  -0.0669   0.7834   1.0000
  -0.750   0.3936   0.02616   0.01593  -0.0659   0.7681   1.0000
  -0.500   0.4138   0.02655   0.01620  -0.0648   0.7540   1.0000
  -0.250   0.4328   0.02707   0.01663  -0.0639   0.7398   1.0000
   0.000   0.4514   0.02763   0.01713  -0.0629   0.7266   1.0000
   0.250   0.4699   0.02822   0.01766  -0.0618   0.7145   1.0000
   0.500   0.4894   0.02870   0.01804  -0.0605   0.7041   1.0000
   0.750   0.5073   0.02940   0.01872  -0.0596   0.6925   1.0000
   1.000   0.5245   0.03022   0.01953  -0.0586   0.6816   1.0000
   1.250   0.5449   0.03064   0.01986  -0.0572   0.6731   1.0000
   1.500   0.5596   0.03175   0.02103  -0.0564   0.6618   1.0000
   1.750   0.5766   0.03262   0.02189  -0.0553   0.6529   1.0000
   2.000   0.5932   0.03349   0.02276  -0.0541   0.6437   1.0000
   2.250   0.6062   0.03475   0.02407  -0.0530   0.6344   1.0000
   2.500   0.6242   0.03548   0.02480  -0.0516   0.6265   1.0000
   2.750   0.6319   0.03724   0.02664  -0.0503   0.6174   1.0000
   3.000   0.6507   0.03789   0.02727  -0.0488   0.6099   1.0000
   3.250   0.6514   0.04015   0.02964  -0.0471   0.6010   1.0000
   3.500   0.6694   0.04092   0.03041  -0.0456   0.5941   1.0000
   3.750   0.6614   0.04372   0.03330  -0.0433   0.5857   1.0000
   4.000   0.6754   0.04478   0.03441  -0.0415   0.5786   1.0000
   4.250   0.6596   0.04793   0.03762  -0.0385   0.5717   1.0000
   4.500   0.6516   0.05033   0.04006  -0.0356   0.5648   1.0000
   4.750   0.6577   0.05195   0.04170  -0.0333   0.5585   1.0000
   5.000   0.6005   0.05666   0.04638  -0.0272   0.5551   1.0000
   5.250   0.5509   0.05993   0.04955  -0.0204   0.5535   1.0000
   5.500   0.5223   0.06253   0.05212  -0.0157   0.5519   1.0000
   5.750   0.5005   0.06505   0.05460  -0.0121   0.5513   1.0000
   6.000   0.4790   0.06777   0.05729  -0.0090   0.5540   1.0000
   6.250   0.4690   0.07036   0.05986  -0.0070   0.5567   1.0000
   6.500   0.4739   0.07301   0.06255  -0.0064   0.5597   1.0000
   8.000   0.4060   0.08920   0.07873  -0.0014   0.6135   1.0000
   8.250   0.4140   0.09140   0.08095  -0.0009   0.6024   1.0000
   8.500   0.4414   0.09499   0.08459  -0.0020   0.5918   1.0000
   8.750   0.4514   0.09695   0.08660  -0.0015   0.5776   1.0000
   9.000   0.4478   0.09832   0.08798  -0.0002   0.5651   1.0000
   9.250   0.4544   0.10072   0.09045   0.0001   0.5545   1.0000
   9.500   0.4785   0.10433   0.09413  -0.0008   0.5434   1.0000
   9.750   0.4879   0.10650   0.09637  -0.0005   0.5301   1.0000
  10.000   0.4831   0.10813   0.09801   0.0003   0.5188   1.0000
  10.250   0.4930   0.11100   0.10093   0.0002   0.5083   1.0000
  10.500   0.5265   0.11564   0.10572  -0.0011   0.4968   1.0000
  10.750   0.5127   0.11627   0.10636   0.0000   0.4850   1.0000
  11.000   0.5161   0.11886   0.10900   0.0000   0.4748   1.0000
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