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EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 583 AIRFOIL (e583-il)
Reynolds number: 100,000
Max Cl/Cd: 32.62 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e583-il-100000-n5.txt
Download as CSV file: xf-e583-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 583 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1571   0.11934   0.11442  -0.0834   0.9264   0.0489
 -11.500  -0.1465   0.11441   0.10946  -0.0893   0.9170   0.0496
 -11.000  -0.1330   0.10345   0.09843  -0.1027   0.8976   0.0503
 -10.500  -0.1080   0.08996   0.08476  -0.1080   0.8803   0.0253
 -10.250  -0.1000   0.08596   0.08072  -0.1109   0.8696   0.0248
 -10.000  -0.0967   0.08130   0.07601  -0.1143   0.8597   0.0242
  -9.750  -0.0974   0.07616   0.07084  -0.1180   0.8503   0.0236
  -9.500  -0.1365   0.06276   0.05731  -0.1279   0.8398   0.0215
  -9.250  -0.1435   0.05920   0.05362  -0.1295   0.8315   0.0213
  -9.000  -0.1574   0.05587   0.05017  -0.1294   0.8222   0.0212
  -8.750  -0.1682   0.05312   0.04725  -0.1284   0.8153   0.0210
  -8.500  -0.1821   0.05070   0.04468  -0.1259   0.8077   0.0209
  -8.250  -0.1920   0.04771   0.04142  -0.1236   0.8014   0.0207
  -8.000  -0.1954   0.04497   0.03838  -0.1215   0.7960   0.0206
  -7.750  -0.1976   0.04230   0.03540  -0.1189   0.7897   0.0205
  -7.500  -0.1940   0.03963   0.03233  -0.1167   0.7847   0.0204
  -7.250  -0.1860   0.03695   0.02919  -0.1147   0.7808   0.0204
  -7.000  -0.1771   0.03473   0.02659  -0.1124   0.7757   0.0206
  -6.750  -0.1627   0.03264   0.02409  -0.1107   0.7713   0.0208
  -6.500  -0.1437   0.03063   0.02162  -0.1095   0.7677   0.0212
  -6.250  -0.1206   0.02893   0.01959  -0.1088   0.7647   0.0217
  -6.000  -0.1019   0.02793   0.01850  -0.1076   0.7600   0.0225
  -5.750  -0.0806   0.02702   0.01745  -0.1067   0.7558   0.0240
  -5.500  -0.0573   0.02602   0.01625  -0.1060   0.7525   0.0263
  -5.250  -0.0332   0.02521   0.01535  -0.1056   0.7497   0.0288
  -5.000  -0.0108   0.02432   0.01434  -0.1046   0.7466   0.0310
  -4.750   0.0068   0.02377   0.01380  -0.1031   0.7422   0.0340
  -4.500   0.0268   0.02322   0.01322  -0.1020   0.7383   0.0395
  -4.250   0.0479   0.02259   0.01255  -0.1009   0.7352   0.0468
  -4.000   0.0704   0.02197   0.01192  -0.1001   0.7327   0.0610
  -3.750   0.0893   0.02145   0.01153  -0.0988   0.7294   0.0861
  -3.500   0.1050   0.02101   0.01135  -0.0970   0.7251   0.1313
  -3.250   0.1214   0.02032   0.01114  -0.0955   0.7215   0.2288
  -3.000   0.1325   0.01921   0.01092  -0.0931   0.7185   0.4279
  -2.750   0.1463   0.01938   0.01215  -0.0876   0.7163   0.6929
  -2.500   0.1617   0.01987   0.01252  -0.0847   0.7127   0.7517
  -2.250   0.1749   0.02047   0.01303  -0.0814   0.7083   0.7826
  -2.000   0.1920   0.02092   0.01334  -0.0786   0.7049   0.8075
  -1.750   0.2145   0.02132   0.01359  -0.0765   0.7021   0.8264
  -1.500   0.2407   0.02174   0.01387  -0.0746   0.6999   0.8488
  -1.250   0.2619   0.02223   0.01426  -0.0720   0.6968   0.8730
  -1.000   0.2836   0.02265   0.01462  -0.0704   0.6924   0.8894
  -0.750   0.3108   0.02275   0.01460  -0.0704   0.6889   0.8961
  -0.500   0.3296   0.02272   0.01445  -0.0690   0.6859   0.9028
  -0.250   0.3643   0.02265   0.01421  -0.0705   0.6837   0.9057
   0.000   0.3868   0.02275   0.01423  -0.0699   0.6804   0.9100
   0.250   0.3850   0.02307   0.01456  -0.0651   0.6747   0.9174
   0.500   0.4128   0.02311   0.01451  -0.0656   0.6713   0.9201
   0.750   0.4430   0.02306   0.01436  -0.0663   0.6687   0.9227
   1.000   0.4746   0.02297   0.01415  -0.0673   0.6666   0.9254
   1.250   0.4675   0.02349   0.01473  -0.0618   0.6600   0.9323
   1.500   0.4912   0.02366   0.01486  -0.0617   0.6560   0.9352
   1.750   0.5208   0.02364   0.01477  -0.0624   0.6531   0.9376
   2.000   0.5534   0.02353   0.01457  -0.0635   0.6509   0.9395
   2.250   0.5503   0.02413   0.01524  -0.0589   0.6444   0.9464
   2.500   0.5722   0.02439   0.01549  -0.0586   0.6398   0.9495
   2.750   0.6031   0.02435   0.01541  -0.0595   0.6369   0.9516
   3.000   0.6378   0.02422   0.01522  -0.0610   0.6348   0.9534
   3.250   0.6348   0.02510   0.01620  -0.0570   0.6269   0.9607
   3.500   0.6620   0.02529   0.01639  -0.0575   0.6228   0.9638
   3.750   0.6969   0.02517   0.01625  -0.0591   0.6202   0.9658
   4.000   0.7353   0.02495   0.01600  -0.0611   0.6182   0.9673
   4.250   0.7282   0.02627   0.01745  -0.0572   0.6084   0.9760
   4.500   0.7634   0.02618   0.01736  -0.0588   0.6053   0.9786
   4.750   0.8040   0.02592   0.01711  -0.0612   0.6031   0.9804
   5.250   0.8344   0.02713   0.01846  -0.0596   0.5897   0.9978
   5.500   0.8718   0.02673   0.01807  -0.0612   0.5873   1.0000
   6.000   0.8531   0.02817   0.01959  -0.0510   0.5725   1.0000
   6.250   0.8944   0.02752   0.01896  -0.0528   0.5706   1.0000
   6.750   0.9098   0.02906   0.02060  -0.0490   0.5558   1.0000
   7.250   0.9330   0.03064   0.02231  -0.0466   0.5409   1.0000
   7.750   0.9607   0.03215   0.02394  -0.0449   0.5259   1.0000
   8.250   0.9926   0.03343   0.02535  -0.0436   0.5108   1.0000
   8.750   1.0272   0.03453   0.02661  -0.0425   0.4956   1.0000
   9.250   1.0657   0.03532   0.02754  -0.0415   0.4801   1.0000
   9.750   1.1080   0.03579   0.02817  -0.0408   0.4639   1.0000
  10.000   1.1103   0.03756   0.03001  -0.0394   0.4519   1.0000
  10.250   1.1295   0.03795   0.03047  -0.0389   0.4426   1.0000
  10.500   1.1553   0.03775   0.03035  -0.0387   0.4337   1.0000
  10.750   1.1623   0.03917   0.03185  -0.0376   0.4214   1.0000
  11.000   1.1784   0.03983   0.03257  -0.0370   0.4103   1.0000
  11.250   1.2034   0.03968   0.03247  -0.0367   0.3998   1.0000
  11.500   1.2145   0.04075   0.03360  -0.0358   0.3871   1.0000
  11.750   1.2222   0.04214   0.03504  -0.0348   0.3736   1.0000
  12.000   1.2314   0.04342   0.03638  -0.0339   0.3603   1.0000
  12.250   1.2405   0.04472   0.03772  -0.0331   0.3465   1.0000
  12.500   1.2486   0.04613   0.03916  -0.0322   0.3322   1.0000
  12.750   1.2560   0.04765   0.04071  -0.0314   0.3181   1.0000
  13.000   1.2623   0.04930   0.04237  -0.0306   0.3041   1.0000
  13.250   1.2675   0.05110   0.04418  -0.0298   0.2899   1.0000
  13.500   1.2721   0.05301   0.04612  -0.0291   0.2761   1.0000
  13.750   1.2754   0.05511   0.04822  -0.0285   0.2622   1.0000
  14.000   1.2766   0.05751   0.05066  -0.0279   0.2485   1.0000
  14.250   1.2772   0.06006   0.05324  -0.0275   0.2351   1.0000
  14.500   1.2774   0.06274   0.05597  -0.0272   0.2219   1.0000
  14.750   1.2771   0.06553   0.05880  -0.0269   0.2091   1.0000
  15.000   1.2762   0.06845   0.06174  -0.0268   0.1965   1.0000
  15.250   1.2747   0.07152   0.06485  -0.0268   0.1844   1.0000
  15.500   1.2725   0.07474   0.06808  -0.0269   0.1728   1.0000
  15.750   1.2697   0.07816   0.07154  -0.0272   0.1614   1.0000
  16.000   1.2668   0.08169   0.07514  -0.0276   0.1504   1.0000
  16.250   1.2636   0.08531   0.07881  -0.0282   0.1402   1.0000
  16.500   1.2593   0.08913   0.08265  -0.0288   0.1305   1.0000
  16.750   1.2551   0.09307   0.08664  -0.0297   0.1211   1.0000
  17.000   1.2514   0.09701   0.09067  -0.0306   0.1123   1.0000
  17.250   1.2465   0.10114   0.09484  -0.0317   0.1044   1.0000
  17.500   1.2419   0.10533   0.09910  -0.0330   0.0967   1.0000
  17.750   1.2379   0.10951   0.10336  -0.0343   0.0896   1.0000
  18.000   1.2323   0.11396   0.10783  -0.0359   0.0834   1.0000
  18.250   1.2288   0.11816   0.11215  -0.0374   0.0770   1.0000
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