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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 500,000
Max Cl/Cd: 112.01 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e582-il-500000.txt
Download as CSV file: xf-e582-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1790   0.11308   0.11077  -0.0800   0.9759   0.0131
 -11.250  -0.1686   0.10890   0.10659  -0.0833   0.9685   0.0135
 -11.000  -0.1581   0.10415   0.10183  -0.0874   0.9610   0.0143
 -10.750  -0.1469   0.09865   0.09632  -0.0931   0.9534   0.0147
 -10.500  -0.1331   0.09186   0.08952  -0.1012   0.9471   0.0150
 -10.250  -0.1152   0.08540   0.08303  -0.1094   0.9410   0.0151
 -10.000  -0.0986   0.07938   0.07698  -0.1167   0.9334   0.0153
  -9.750  -0.0736   0.07650   0.07404  -0.1216   0.9239   0.0159
  -9.500  -0.0549   0.07157   0.06903  -0.1288   0.9093   0.0161
  -9.250  -0.0459   0.06720   0.06456  -0.1335   0.8918   0.0167
  -9.000  -0.0478   0.06243   0.05971  -0.1375   0.8751   0.0167
  -8.750  -0.0619   0.05669   0.05387  -0.1421   0.8597   0.0168
  -8.500  -0.0785   0.05264   0.04970  -0.1430   0.8474   0.0167
  -8.250  -0.0964   0.04969   0.04662  -0.1413   0.8372   0.0168
  -8.000  -0.1072   0.04663   0.04343  -0.1396   0.8286   0.0172
  -7.750  -0.1126   0.04319   0.03978  -0.1380   0.8221   0.0179
  -7.500  -0.1244   0.03917   0.03517  -0.1342   0.8147   0.0191
  -7.250  -0.1252   0.03473   0.03056  -0.1327   0.8097   0.0196
  -7.000  -0.1124   0.03299   0.02877  -0.1318   0.8049   0.0200
  -6.750  -0.0987   0.03139   0.02706  -0.1308   0.8002   0.0205
  -6.500  -0.1028   0.02213   0.01658  -0.1248   0.7958   0.0115
  -6.250  -0.0843   0.01967   0.01376  -0.1236   0.7920   0.0112
  -6.000  -0.0628   0.01798   0.01178  -0.1225   0.7879   0.0113
  -5.750  -0.0389   0.01683   0.01039  -0.1218   0.7841   0.0115
  -5.500  -0.0139   0.01591   0.00927  -0.1213   0.7807   0.0116
  -5.250   0.0113   0.01497   0.00818  -0.1210   0.7775   0.0119
  -5.000   0.0345   0.01422   0.00746  -0.1205   0.7737   0.0129
  -4.750   0.0594   0.01373   0.00694  -0.1201   0.7700   0.0138
  -4.500   0.0840   0.01312   0.00625  -0.1196   0.7666   0.0142
  -4.250   0.1092   0.01260   0.00565  -0.1192   0.7634   0.0146
  -4.000   0.1336   0.01213   0.00513  -0.1187   0.7600   0.0152
  -3.750   0.1577   0.01161   0.00461  -0.1182   0.7564   0.0170
  -3.500   0.1835   0.01122   0.00419  -0.1180   0.7529   0.0220
  -3.250   0.2084   0.01062   0.00378  -0.1177   0.7497   0.0698
  -3.000   0.2339   0.01014   0.00361  -0.1178   0.7466   0.1544
  -2.750   0.2569   0.00939   0.00345  -0.1178   0.7430   0.3127
  -2.500   0.2768   0.00801   0.00342  -0.1173   0.7393   0.6745
  -2.250   0.3034   0.00827   0.00373  -0.1167   0.7360   0.7556
  -2.000   0.3313   0.00853   0.00390  -0.1164   0.7330   0.7742
  -1.750   0.3580   0.00874   0.00407  -0.1160   0.7296   0.7873
  -1.500   0.3841   0.00896   0.00425  -0.1154   0.7259   0.7996
  -1.250   0.4088   0.00916   0.00444  -0.1144   0.7223   0.8075
  -1.000   0.4367   0.00931   0.00450  -0.1143   0.7191   0.8161
  -0.750   0.4615   0.00950   0.00467  -0.1134   0.7158   0.8217
  -0.500   0.4867   0.00966   0.00481  -0.1127   0.7119   0.8310
  -0.250   0.5061   0.00989   0.00507  -0.1102   0.7081   0.8407
   0.000   0.5282   0.01005   0.00521  -0.1086   0.7046   0.8499
   0.250   0.5535   0.01020   0.00530  -0.1079   0.7012   0.8556
   0.500   0.5805   0.01019   0.00528  -0.1080   0.6971   0.8589
   0.750   0.6093   0.01016   0.00522  -0.1085   0.6928   0.8611
   1.000   0.6361   0.01011   0.00513  -0.1084   0.6889   0.8626
   1.250   0.6634   0.01013   0.00511  -0.1084   0.6850   0.8641
   1.500   0.6891   0.01009   0.00509  -0.1082   0.6803   0.8656
   1.750   0.7165   0.01007   0.00505  -0.1084   0.6759   0.8670
   2.000   0.7455   0.01008   0.00501  -0.1088   0.6720   0.8682
   2.250   0.7724   0.01007   0.00502  -0.1089   0.6673   0.8697
   2.500   0.7999   0.01005   0.00500  -0.1092   0.6621   0.8708
   2.750   0.8287   0.01004   0.00495  -0.1097   0.6574   0.8721
   3.000   0.8560   0.01005   0.00497  -0.1099   0.6519   0.8733
   3.250   0.8837   0.01004   0.00497  -0.1102   0.6462   0.8742
   3.750   0.9383   0.01005   0.00498  -0.1106   0.6347   0.8761
   4.000   0.9642   0.01004   0.00497  -0.1105   0.6286   0.8770
   4.250   0.9899   0.01006   0.00501  -0.1103   0.6221   0.8779
   4.500   1.0152   0.01007   0.00504  -0.1101   0.6149   0.8787
   4.750   1.0407   0.01011   0.00509  -0.1099   0.6079   0.8796
   5.000   1.0653   0.01015   0.00516  -0.1095   0.5997   0.8806
   5.250   1.0896   0.01021   0.00524  -0.1091   0.5913   0.8818
   5.500   1.1137   0.01029   0.00531  -0.1087   0.5825   0.8831
   5.750   1.1372   0.01037   0.00543  -0.1081   0.5725   0.8842
   6.000   1.1605   0.01048   0.00554  -0.1075   0.5624   0.8853
   6.250   1.1827   0.01062   0.00567  -0.1068   0.5513   0.8865
   6.500   1.2040   0.01075   0.00583  -0.1058   0.5387   0.8877
   6.750   1.2243   0.01093   0.00600  -0.1047   0.5250   0.8889
   7.000   1.2424   0.01113   0.00619  -0.1032   0.5105   0.8901
   7.250   1.2562   0.01133   0.00638  -0.1007   0.4946   0.8916
   7.500   1.2683   0.01163   0.00665  -0.0980   0.4775   0.8936
   7.750   1.2806   0.01199   0.00699  -0.0954   0.4588   0.8955
   8.000   1.2928   0.01240   0.00737  -0.0929   0.4397   0.8973
   8.250   1.3031   0.01291   0.00782  -0.0901   0.4199   0.8994
   8.500   1.3123   0.01349   0.00836  -0.0873   0.3991   0.9016
   8.750   1.3214   0.01414   0.00895  -0.0847   0.3777   0.9038
   9.250   1.3342   0.01566   0.01036  -0.0787   0.3359   0.9087
   9.500   1.3394   0.01657   0.01121  -0.0757   0.3149   0.9117
   9.750   1.3446   0.01756   0.01214  -0.0730   0.2943   0.9151
  10.000   1.3506   0.01862   0.01315  -0.0705   0.2734   0.9188
  10.250   1.3539   0.01975   0.01424  -0.0677   0.2540   0.9229
  10.500   1.3584   0.02092   0.01537  -0.0652   0.2356   0.9276
  10.750   1.3641   0.02213   0.01654  -0.0631   0.2175   0.9328
  11.000   1.3688   0.02333   0.01774  -0.0608   0.2014   0.9402
  11.250   1.3740   0.02469   0.01907  -0.0589   0.1841   0.9524
  11.500   1.3805   0.02617   0.02053  -0.0577   0.1672   1.0000
  11.750   1.3875   0.02777   0.02207  -0.0565   0.1508   1.0000
  12.000   1.3939   0.02944   0.02369  -0.0554   0.1345   1.0000
  12.250   1.3993   0.03121   0.02540  -0.0543   0.1190   1.0000
  12.500   1.4032   0.03314   0.02726  -0.0531   0.1031   1.0000
  12.750   1.4059   0.03520   0.02924  -0.0519   0.0881   1.0000
  13.500   1.4150   0.04163   0.03554  -0.0489   0.0532   1.0000
  13.750   1.4184   0.04384   0.03774  -0.0481   0.0449   1.0000
  14.000   1.4202   0.04625   0.04012  -0.0474   0.0366   1.0000
  14.250   1.4237   0.04858   0.04247  -0.0468   0.0310   1.0000
  14.500   1.4267   0.05103   0.04495  -0.0463   0.0270   1.0000
  14.750   1.4287   0.05361   0.04755  -0.0459   0.0232   1.0000
  15.000   1.4319   0.05614   0.05014  -0.0456   0.0203   1.0000
  15.250   1.4324   0.05904   0.05307  -0.0453   0.0176   1.0000
  15.500   1.4359   0.06166   0.05579  -0.0453   0.0154   1.0000
  15.750   1.4352   0.06484   0.05902  -0.0453   0.0135   1.0000
  16.000   1.4373   0.06774   0.06201  -0.0454   0.0118   1.0000
  16.250   1.4353   0.07124   0.06557  -0.0456   0.0101   1.0000
  16.500   1.4341   0.07472   0.06914  -0.0460   0.0084   1.0000
  16.750   1.4313   0.07852   0.07302  -0.0466   0.0072   1.0000
  17.000   1.4243   0.08298   0.07755  -0.0473   0.0058   1.0000
  17.250   1.4216   0.08692   0.08163  -0.0482   0.0050   1.0000
  17.500   1.4130   0.09185   0.08665  -0.0494   0.0042   1.0000
  17.750   1.4062   0.09666   0.09159  -0.0507   0.0038   1.0000
  18.000   1.4004   0.10138   0.09643  -0.0522   0.0032   1.0000
  18.250   1.3915   0.10668   0.10184  -0.0540   0.0029   1.0000
  18.500   1.3792   0.11271   0.10801  -0.0563   0.0027   1.0000
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