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EPPLER 361 AIRFOIL (e361-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 361 AIRFOIL (e361-il)
Reynolds number: 50,000
Max Cl/Cd: 31.52 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e361-il-50000-n5.txt
Download as CSV file: xf-e361-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 361 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.3919   0.13053   0.12369  -0.0103   1.0000   0.0590
 -12.000  -0.4084   0.12503   0.11820  -0.0149   1.0000   0.0517
 -11.750  -0.5082   0.12793   0.12052  -0.0100   1.0000   0.0512
 -11.500  -0.4994   0.12421   0.11682  -0.0102   1.0000   0.0497
 -11.250  -0.4958   0.12005   0.11269  -0.0116   1.0000   0.0481
 -11.000  -0.4958   0.11526   0.10796  -0.0138   1.0000   0.0466
 -10.750  -0.5121   0.10672   0.09949  -0.0206   1.0000   0.0430
 -10.500  -0.5087   0.10275   0.09557  -0.0217   1.0000   0.0425
 -10.250  -0.5088   0.09807   0.09094  -0.0237   1.0000   0.0420
 -10.000  -0.5105   0.09312   0.08604  -0.0263   1.0000   0.0414
  -9.750  -0.5161   0.08731   0.08027  -0.0300   1.0000   0.0407
  -9.500  -0.5272   0.08163   0.07461  -0.0336   1.0000   0.0401
  -9.250  -0.5423   0.07657   0.06954  -0.0360   1.0000   0.0395
  -9.000  -0.5603   0.07218   0.06512  -0.0365   1.0000   0.0390
  -8.750  -0.5770   0.06851   0.06138  -0.0354   1.0000   0.0386
  -8.500  -0.5903   0.06463   0.05735  -0.0341   1.0000   0.0382
  -8.250  -0.5997   0.06089   0.05339  -0.0324   1.0000   0.0378
  -8.000  -0.6052   0.05731   0.04954  -0.0304   1.0000   0.0374
  -7.750  -0.6059   0.05407   0.04606  -0.0283   1.0000   0.0377
  -7.500  -0.6034   0.05114   0.04286  -0.0261   1.0000   0.0381
  -7.250  -0.5988   0.04840   0.03986  -0.0238   1.0000   0.0389
  -7.000  -0.5928   0.04577   0.03691  -0.0213   1.0000   0.0398
  -6.750  -0.5858   0.04319   0.03397  -0.0186   1.0000   0.0411
  -6.500  -0.5768   0.04076   0.03115  -0.0159   1.0000   0.0420
  -6.250  -0.5657   0.03853   0.02852  -0.0133   1.0000   0.0427
  -6.000  -0.5533   0.03643   0.02624  -0.0110   1.0000   0.0437
  -5.750  -0.5409   0.03481   0.02450  -0.0088   1.0000   0.0448
  -5.500  -0.5295   0.03350   0.02308  -0.0064   1.0000   0.0466
  -5.250  -0.5168   0.03228   0.02167  -0.0041   0.9996   0.0493
  -5.000  -0.4763   0.03035   0.01956  -0.0066   0.9886   0.0547
  -4.750  -0.4348   0.02875   0.01774  -0.0089   0.9778   0.0627
  -4.500  -0.3952   0.02733   0.01625  -0.0111   0.9666   0.0742
  -4.250  -0.3578   0.02589   0.01487  -0.0132   0.9553   0.0928
  -4.000  -0.3221   0.02440   0.01349  -0.0152   0.9440   0.1282
  -3.750  -0.2956   0.02237   0.01229  -0.0162   0.9312   0.2292
  -3.500  -0.2774   0.02033   0.01259  -0.0130   0.9210   0.6327
  -3.250  -0.2332   0.02125   0.01346  -0.0121   0.9137   0.7870
  -3.000  -0.1648   0.02283   0.01467  -0.0147   0.9109   0.8672
  -2.750  -0.0854   0.02342   0.01479  -0.0221   0.9072   0.9043
  -2.500  -0.0279   0.02331   0.01431  -0.0275   0.8980   0.9215
  -2.250   0.0211   0.02310   0.01381  -0.0319   0.8863   0.9340
  -2.000   0.0647   0.02289   0.01336  -0.0353   0.8747   0.9450
  -1.750   0.1087   0.02263   0.01286  -0.0388   0.8635   0.9544
  -1.500   0.1486   0.02241   0.01245  -0.0416   0.8510   0.9631
  -1.250   0.1842   0.02227   0.01215  -0.0437   0.8391   0.9720
  -1.000   0.2230   0.02203   0.01177  -0.0464   0.8282   0.9794
  -0.750   0.2588   0.02186   0.01147  -0.0485   0.8174   0.9867
  -0.500   0.2933   0.02174   0.01126  -0.0505   0.8062   0.9940
  -0.250   0.3274   0.02161   0.01103  -0.0523   0.7962   1.0000
   0.000   0.3473   0.02169   0.01106  -0.0514   0.7856   1.0000
   0.250   0.3664   0.02184   0.01116  -0.0504   0.7750   1.0000
   0.500   0.3867   0.02194   0.01121  -0.0494   0.7660   1.0000
   0.750   0.4053   0.02213   0.01139  -0.0483   0.7555   1.0000
   1.000   0.4245   0.02231   0.01156  -0.0471   0.7461   1.0000
   1.250   0.4446   0.02247   0.01171  -0.0461   0.7369   1.0000
   1.500   0.4633   0.02272   0.01197  -0.0450   0.7267   1.0000
   2.000   0.5015   0.02313   0.01242  -0.0423   0.7069   1.0000
   2.250   0.5197   0.02334   0.01266  -0.0408   0.6963   1.0000
   2.500   0.5395   0.02342   0.01272  -0.0391   0.6861   1.0000
   2.750   0.5558   0.02365   0.01299  -0.0372   0.6729   1.0000
   3.250   0.5899   0.02388   0.01329  -0.0330   0.6453   1.0000
   3.500   0.6073   0.02392   0.01334  -0.0307   0.6305   1.0000
   3.750   0.6245   0.02393   0.01337  -0.0284   0.6150   1.0000
   4.000   0.6416   0.02394   0.01340  -0.0261   0.5989   1.0000
   4.250   0.6584   0.02395   0.01347  -0.0238   0.5820   1.0000
   4.500   0.6750   0.02396   0.01353  -0.0214   0.5645   1.0000
   4.750   0.6916   0.02397   0.01358  -0.0190   0.5461   1.0000
   5.000   0.7085   0.02395   0.01361  -0.0166   0.5268   1.0000
   5.250   0.7229   0.02408   0.01380  -0.0141   0.5044   1.0000
   5.500   0.7383   0.02413   0.01389  -0.0116   0.4803   1.0000
   5.750   0.7522   0.02428   0.01407  -0.0090   0.4517   1.0000
   6.000   0.7661   0.02444   0.01421  -0.0063   0.4196   1.0000
   6.250   0.7792   0.02472   0.01436  -0.0035   0.3841   1.0000
   6.500   0.7907   0.02520   0.01464  -0.0007   0.3473   1.0000
   6.750   0.8009   0.02591   0.01510   0.0021   0.3146   1.0000
   7.000   0.8107   0.02680   0.01580   0.0048   0.2878   1.0000
   7.250   0.8201   0.02778   0.01659   0.0073   0.2660   1.0000
   7.500   0.8307   0.02880   0.01747   0.0096   0.2481   1.0000
   7.750   0.8426   0.02984   0.01842   0.0116   0.2331   1.0000
   8.000   0.8555   0.03087   0.01944   0.0135   0.2196   1.0000
   8.250   0.8696   0.03192   0.02051   0.0152   0.2075   1.0000
   8.500   0.8852   0.03300   0.02161   0.0166   0.1972   1.0000
   8.750   0.9024   0.03407   0.02260   0.0179   0.1881   1.0000
   9.000   0.9182   0.03521   0.02393   0.0192   0.1789   1.0000
   9.250   0.9369   0.03637   0.02510   0.0202   0.1713   1.0000
   9.500   0.9538   0.03763   0.02651   0.0213   0.1639   1.0000
   9.750   0.9728   0.03888   0.02778   0.0221   0.1572   1.0000
  10.000   0.9864   0.04034   0.02948   0.0234   0.1506   1.0000
  10.250   1.0080   0.04164   0.03074   0.0239   0.1450   1.0000
  10.500   1.0166   0.04342   0.03285   0.0255   0.1396   1.0000
  10.750   1.0279   0.04502   0.03461   0.0268   0.1344   1.0000
  11.000   1.0476   0.04657   0.03614   0.0273   0.1297   1.0000
  11.250   1.0448   0.04879   0.03875   0.0297   0.1261   1.0000
  11.500   1.0453   0.05090   0.04110   0.0316   0.1223   1.0000
  11.750   1.0547   0.05263   0.04289   0.0327   0.1184   1.0000
  12.000   1.0600   0.05488   0.04526   0.0339   0.1153   1.0000
  12.250   1.0442   0.05823   0.04896   0.0354   0.1134   1.0000
  12.500   1.0270   0.06201   0.05302   0.0361   0.1115   1.0000
  12.750   1.0077   0.06635   0.05760   0.0359   0.1099   1.0000
  13.000   0.9835   0.07157   0.06303   0.0348   0.1086   1.0000
  13.250   0.9449   0.07929   0.07095   0.0317   0.1085   1.0000
  13.500   0.8472   0.09871   0.09048   0.0201   0.1109   1.0000
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