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E205 (10.48%) (e205-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: E205 (10.48%) (e205-il)
Reynolds number: 500,000
Max Cl/Cd: 105.4 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e205-il-500000.txt
Download as CSV file: xf-e205-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E205  (10.48%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4084   0.08542   0.08324  -0.0297   1.0000   0.0226
  -8.750  -0.4084   0.08184   0.07969  -0.0313   1.0000   0.0235
  -8.500  -0.4113   0.07786   0.07575  -0.0333   1.0000   0.0240
  -8.250  -0.4167   0.07389   0.07182  -0.0354   1.0000   0.0242
  -8.000  -0.4313   0.06946   0.06744  -0.0380   1.0000   0.0248
  -7.000  -0.4376   0.04174   0.03910  -0.0544   0.9885   0.0283
  -6.750  -0.4077   0.03910   0.03634  -0.0578   0.9820   0.0293
  -6.500  -0.3792   0.03589   0.03293  -0.0607   0.9714   0.0311
  -6.000  -0.3456   0.01950   0.01445  -0.0596   0.9296   0.0208
  -5.750  -0.3179   0.01822   0.01289  -0.0593   0.9041   0.0204
  -5.500  -0.2941   0.01683   0.01120  -0.0584   0.8756   0.0204
  -5.250  -0.2721   0.01517   0.00925  -0.0572   0.8488   0.0209
  -5.000  -0.2487   0.01414   0.00798  -0.0561   0.8241   0.0210
  -4.750  -0.2249   0.01328   0.00692  -0.0551   0.8013   0.0211
  -4.250  -0.1769   0.01192   0.00528  -0.0533   0.7628   0.0223
  -4.000  -0.1521   0.01147   0.00469  -0.0525   0.7460   0.0231
  -3.750  -0.1269   0.01108   0.00419  -0.0519   0.7308   0.0240
  -3.500  -0.1013   0.01074   0.00374  -0.0513   0.7170   0.0250
  -3.250  -0.0752   0.01051   0.00339  -0.0508   0.7043   0.0265
  -2.750  -0.0231   0.00989   0.00261  -0.0498   0.6815   0.0366
  -2.500   0.0019   0.00937   0.00233  -0.0493   0.6714   0.0990
  -2.250   0.0275   0.00908   0.00218  -0.0489   0.6622   0.1567
  -2.000   0.0532   0.00876   0.00206  -0.0486   0.6530   0.2252
  -1.750   0.0782   0.00839   0.00198  -0.0482   0.6446   0.3201
  -1.500   0.1030   0.00805   0.00191  -0.0477   0.6364   0.4169
  -1.250   0.1263   0.00759   0.00187  -0.0469   0.6288   0.5482
  -1.000   0.1461   0.00703   0.00186  -0.0452   0.6217   0.7173
  -0.750   0.1694   0.00661   0.00194  -0.0436   0.6147   0.8733
  -0.500   0.2264   0.00674   0.00205  -0.0493   0.6067   0.9588
  -0.250   0.2728   0.00686   0.00208  -0.0530   0.5994   0.9783
   0.000   0.3202   0.00695   0.00206  -0.0572   0.5919   0.9886
   0.250   0.3696   0.00699   0.00202  -0.0619   0.5846   0.9970
   0.500   0.4056   0.00703   0.00197  -0.0637   0.5779   1.0000
   0.750   0.4304   0.00708   0.00196  -0.0631   0.5718   1.0000
   1.000   0.4552   0.00712   0.00196  -0.0625   0.5655   1.0000
   1.250   0.4800   0.00721   0.00197  -0.0619   0.5597   1.0000
   1.500   0.5051   0.00725   0.00200  -0.0613   0.5533   1.0000
   1.750   0.5301   0.00733   0.00203  -0.0607   0.5476   1.0000
   2.000   0.5552   0.00740   0.00208  -0.0602   0.5415   1.0000
   2.250   0.5803   0.00747   0.00213  -0.0596   0.5354   1.0000
   2.500   0.6053   0.00758   0.00220  -0.0590   0.5295   1.0000
   2.750   0.6305   0.00764   0.00226  -0.0585   0.5226   1.0000
   3.000   0.6554   0.00776   0.00233  -0.0578   0.5162   1.0000
   3.250   0.6806   0.00781   0.00241  -0.0573   0.5087   1.0000
   3.500   0.7054   0.00794   0.00249  -0.0567   0.5017   1.0000
   3.750   0.7306   0.00799   0.00258  -0.0561   0.4939   1.0000
   4.000   0.7554   0.00812   0.00267  -0.0555   0.4866   1.0000
   4.250   0.7805   0.00819   0.00279  -0.0549   0.4782   1.0000
   4.500   0.8053   0.00831   0.00290  -0.0543   0.4705   1.0000
   4.750   0.8300   0.00841   0.00301  -0.0537   0.4615   1.0000
   5.000   0.8549   0.00852   0.00314  -0.0531   0.4523   1.0000
   5.250   0.8793   0.00866   0.00329  -0.0524   0.4430   1.0000
   5.500   0.9038   0.00879   0.00343  -0.0518   0.4323   1.0000
   5.750   0.9283   0.00892   0.00359  -0.0511   0.4209   1.0000
   6.000   0.9524   0.00908   0.00375  -0.0504   0.4075   1.0000
   6.250   0.9760   0.00926   0.00394  -0.0496   0.3915   1.0000
   6.500   0.9989   0.00950   0.00414  -0.0487   0.3706   1.0000
   6.750   1.0208   0.00982   0.00438  -0.0477   0.3430   1.0000
   7.000   1.0413   0.01026   0.00468  -0.0465   0.3054   1.0000
   7.250   1.0592   0.01093   0.00513  -0.0450   0.2571   1.0000
   7.500   1.0762   0.01169   0.00566  -0.0434   0.2106   1.0000
   7.750   1.0927   0.01250   0.00625  -0.0418   0.1690   1.0000
   8.000   1.1092   0.01330   0.00686  -0.0402   0.1339   1.0000
   8.250   1.1258   0.01407   0.00748  -0.0386   0.1032   1.0000
   8.500   1.1419   0.01485   0.00813  -0.0370   0.0777   1.0000
   8.750   1.1573   0.01566   0.00882  -0.0352   0.0557   1.0000
   9.000   1.1673   0.01681   0.00976  -0.0328   0.0277   1.0000
   9.250   1.1769   0.01794   0.01081  -0.0301   0.0159   1.0000
   9.500   1.1909   0.01870   0.01164  -0.0281   0.0137   1.0000
   9.750   1.2026   0.01951   0.01251  -0.0258   0.0127   1.0000
  10.000   1.2060   0.02057   0.01366  -0.0222   0.0116   1.0000
  10.250   1.2133   0.02145   0.01465  -0.0194   0.0112   1.0000
  10.500   1.2193   0.02248   0.01577  -0.0168   0.0109   1.0000
  10.750   1.2241   0.02367   0.01706  -0.0143   0.0106   1.0000
  11.000   1.2272   0.02508   0.01856  -0.0120   0.0102   1.0000
  11.250   1.2335   0.02639   0.01993  -0.0104   0.0096   1.0000
  11.500   1.2343   0.02825   0.02189  -0.0087   0.0093   1.0000
  11.750   1.2361   0.03020   0.02393  -0.0075   0.0093   1.0000
  12.000   1.2341   0.03262   0.02644  -0.0064   0.0089   1.0000
  12.250   1.2259   0.03580   0.02973  -0.0053   0.0087   1.0000
  12.500   1.2240   0.03850   0.03253  -0.0046   0.0086   1.0000
  12.750   1.2225   0.04121   0.03534  -0.0039   0.0085   1.0000
  13.000   1.2269   0.04340   0.03766  -0.0037   0.0084   1.0000
  13.250   1.2285   0.04594   0.04031  -0.0033   0.0083   1.0000
  13.500   1.2304   0.04846   0.04294  -0.0032   0.0083   1.0000
  13.750   1.2294   0.05134   0.04593  -0.0027   0.0083   1.0000
  14.000   1.2311   0.05404   0.04875  -0.0028   0.0081   1.0000
  14.250   1.2309   0.05698   0.05180  -0.0028   0.0081   1.0000
  14.500   1.2304   0.06009   0.05505  -0.0031   0.0080   1.0000
  14.750   1.2287   0.06340   0.05849  -0.0033   0.0081   1.0000
  15.000   1.2262   0.06698   0.06222  -0.0040   0.0079   1.0000
  15.250   1.2225   0.07084   0.06623  -0.0048   0.0078   1.0000
  15.500   1.2177   0.07496   0.07050  -0.0060   0.0077   1.0000
  15.750   1.2111   0.07948   0.07518  -0.0072   0.0079   1.0000
  16.000   1.2029   0.08446   0.08033  -0.0091   0.0078   1.0000
  16.250   1.1931   0.08986   0.08590  -0.0112   0.0078   1.0000
  16.500   1.1821   0.09566   0.09186  -0.0137   0.0079   1.0000
  16.750   1.1691   0.10210   0.09849  -0.0168   0.0079   1.0000
  17.000   1.1556   0.10882   0.10537  -0.0202   0.0079   1.0000
  17.250   1.1409   0.11611   0.11283  -0.0241   0.0079   1.0000
  17.500   1.1243   0.12412   0.12102  -0.0287   0.0079   1.0000
  17.750   1.1077   0.13243   0.12948  -0.0335   0.0080   1.0000
  18.000   1.0911   0.14102   0.13821  -0.0386   0.0081   1.0000
  18.250   1.0738   0.15024   0.14758  -0.0442   0.0082   1.0000
  18.500   1.0556   0.16018   0.15765  -0.0503   0.0083   1.0000
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