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EPPLER 657 AIRFOIL (e657-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 657 AIRFOIL (e657-il)
Reynolds number: 500,000
Max Cl/Cd: 126.17 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e657-il-500000.txt
Download as CSV file: xf-e657-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 657 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0479   0.09251   0.08907  -0.1234   0.8027   0.0220
 -11.000  -0.0704   0.08318   0.07980  -0.1289   0.8005   0.0232
 -10.750  -0.0634   0.08107   0.07768  -0.1292   0.7986   0.0235
 -10.500  -0.0550   0.07926   0.07586  -0.1296   0.7966   0.0238
 -10.250  -0.0503   0.07661   0.07320  -0.1307   0.7946   0.0241
 -10.000  -0.0490   0.07332   0.06990  -0.1323   0.7924   0.0245
  -9.750  -0.0522   0.06922   0.06585  -0.1343   0.7904   0.0249
  -9.500  -0.0598   0.06420   0.06087  -0.1371   0.7883   0.0255
  -9.250  -0.0881   0.05458   0.05127  -0.1449   0.7856   0.0253
  -9.000  -0.1183   0.04908   0.04567  -0.1470   0.7828   0.0253
  -8.750  -0.1414   0.04601   0.04249  -0.1452   0.7803   0.0254
  -8.500  -0.1599   0.04298   0.03928  -0.1429   0.7781   0.0260
  -8.000  -0.2328   0.02433   0.01859  -0.1316   0.7732   0.0129
  -7.750  -0.2156   0.02238   0.01646  -0.1306   0.7715   0.0127
  -7.500  -0.1963   0.02072   0.01458  -0.1298   0.7699   0.0124
  -7.250  -0.1749   0.01938   0.01305  -0.1291   0.7683   0.0123
  -7.000  -0.1523   0.01824   0.01174  -0.1285   0.7668   0.0122
  -6.750  -0.1290   0.01729   0.01065  -0.1279   0.7653   0.0124
  -6.500  -0.1052   0.01651   0.00977  -0.1275   0.7637   0.0125
  -6.250  -0.0809   0.01584   0.00900  -0.1271   0.7622   0.0128
  -6.000  -0.0564   0.01529   0.00836  -0.1267   0.7607   0.0131
  -5.750  -0.0334   0.01464   0.00770  -0.1263   0.7592   0.0140
  -5.500  -0.0086   0.01420   0.00725  -0.1260   0.7580   0.0152
  -5.250   0.0159   0.01372   0.00674  -0.1257   0.7565   0.0167
  -5.000   0.0416   0.01338   0.00639  -0.1256   0.7548   0.0192
  -4.750   0.0670   0.01295   0.00599  -0.1254   0.7531   0.0248
  -4.500   0.0927   0.01253   0.00566  -0.1253   0.7515   0.0424
  -4.250   0.1189   0.01219   0.00544  -0.1254   0.7500   0.0667
  -4.000   0.1457   0.01188   0.00525  -0.1255   0.7485   0.0987
  -3.750   0.1725   0.01155   0.00508  -0.1258   0.7469   0.1444
  -3.500   0.1994   0.01119   0.00495  -0.1261   0.7455   0.2102
  -3.250   0.2264   0.01084   0.00486  -0.1265   0.7442   0.2911
  -3.000   0.2534   0.01055   0.00485  -0.1268   0.7426   0.3790
  -2.750   0.2796   0.01015   0.00479  -0.1271   0.7411   0.4757
  -2.500   0.3060   0.00982   0.00479  -0.1272   0.7394   0.5749
  -2.250   0.3325   0.00964   0.00487  -0.1271   0.7375   0.6556
  -2.000   0.3595   0.00962   0.00497  -0.1269   0.7356   0.7083
  -1.750   0.3869   0.00964   0.00503  -0.1268   0.7337   0.7384
  -1.500   0.4141   0.00970   0.00512  -0.1266   0.7319   0.7597
  -1.250   0.4421   0.00981   0.00521  -0.1265   0.7302   0.7767
  -1.000   0.4708   0.00995   0.00530  -0.1266   0.7286   0.7909
  -0.750   0.4995   0.01015   0.00545  -0.1267   0.7268   0.8026
  -0.500   0.5263   0.01031   0.00559  -0.1265   0.7247   0.8127
  -0.250   0.5530   0.01042   0.00570  -0.1263   0.7223   0.8222
   0.000   0.5787   0.01049   0.00579  -0.1259   0.7197   0.8288
   0.250   0.6062   0.01055   0.00582  -0.1258   0.7173   0.8368
   0.500   0.6329   0.01056   0.00583  -0.1255   0.7150   0.8427
   0.750   0.6607   0.01060   0.00583  -0.1254   0.7129   0.8496
   1.000   0.6893   0.01065   0.00585  -0.1255   0.7109   0.8561
   1.250   0.7134   0.01074   0.00596  -0.1247   0.7082   0.8617
   1.500   0.7391   0.01078   0.00603  -0.1244   0.7050   0.8686
   1.750   0.7630   0.01075   0.00603  -0.1236   0.7019   0.8738
   2.000   0.7893   0.01071   0.00598  -0.1232   0.6991   0.8792
   2.250   0.8194   0.01067   0.00591  -0.1238   0.6965   0.8842
   2.500   0.8483   0.01067   0.00586  -0.1240   0.6940   0.8878
   2.750   0.8699   0.01064   0.00591  -0.1229   0.6903   0.8921
   3.000   0.8953   0.01061   0.00592  -0.1225   0.6865   0.8968
   3.250   0.9246   0.01054   0.00584  -0.1230   0.6830   0.9011
   3.500   0.9513   0.01041   0.00569  -0.1227   0.6798   0.9045
   3.750   0.9756   0.01038   0.00568  -0.1221   0.6758   0.9086
   4.000   0.9998   0.01032   0.00569  -0.1216   0.6709   0.9132
   4.250   1.0274   0.01022   0.00559  -0.1217   0.6666   0.9168
   4.500   1.0538   0.01011   0.00546  -0.1214   0.6628   0.9202
   4.750   1.0741   0.01008   0.00552  -0.1200   0.6569   0.9249
   5.000   1.0995   0.01000   0.00547  -0.1197   0.6512   0.9290
   5.250   1.1239   0.00991   0.00539  -0.1191   0.6456   0.9328
   5.500   1.1427   0.00985   0.00541  -0.1175   0.6380   0.9376
   5.750   1.1665   0.00979   0.00534  -0.1168   0.6309   0.9421
   6.000   1.1847   0.00976   0.00538  -0.1150   0.6211   0.9472
   6.250   1.2033   0.00974   0.00539  -0.1133   0.6112   0.9526
   6.500   1.2226   0.00977   0.00542  -0.1119   0.5998   0.9579
   6.750   1.2377   0.00981   0.00546  -0.1095   0.5862   0.9642
   7.000   1.2517   0.00994   0.00558  -0.1071   0.5700   0.9720
   7.250   1.2708   0.01019   0.00581  -0.1059   0.5508   0.9841
   7.500   1.2863   0.01059   0.00614  -0.1043   0.5289   1.0000
   7.750   1.2977   0.01116   0.00661  -0.1020   0.5069   1.0000
   8.000   1.3071   0.01183   0.00721  -0.0995   0.4831   1.0000
   8.500   1.3214   0.01355   0.00876  -0.0943   0.4395   1.0000
   8.750   1.3276   0.01456   0.00969  -0.0917   0.4186   1.0000
   9.000   1.3317   0.01573   0.01078  -0.0891   0.3978   1.0000
   9.250   1.3372   0.01690   0.01188  -0.0867   0.3773   1.0000
   9.500   1.3431   0.01811   0.01302  -0.0845   0.3576   1.0000
   9.750   1.3486   0.01939   0.01423  -0.0824   0.3383   1.0000
  10.000   1.3532   0.02075   0.01551  -0.0802   0.3192   1.0000
  10.250   1.3584   0.02211   0.01681  -0.0781   0.3013   1.0000
  10.500   1.3647   0.02345   0.01809  -0.0763   0.2835   1.0000
  10.750   1.3714   0.02479   0.01937  -0.0745   0.2660   1.0000
  11.000   1.3774   0.02621   0.02073  -0.0728   0.2483   1.0000
  11.250   1.3844   0.02760   0.02206  -0.0712   0.2324   1.0000
  11.500   1.3904   0.02910   0.02351  -0.0696   0.2156   1.0000
  11.750   1.3977   0.03054   0.02490  -0.0682   0.2008   1.0000
  12.000   1.4043   0.03208   0.02639  -0.0668   0.1860   1.0000
  12.250   1.4113   0.03362   0.02788  -0.0655   0.1716   1.0000
  12.500   1.4181   0.03522   0.02945  -0.0642   0.1589   1.0000
  12.750   1.4251   0.03684   0.03104  -0.0631   0.1468   1.0000
  13.000   1.4309   0.03860   0.03276  -0.0619   0.1349   1.0000
  13.250   1.4387   0.04023   0.03438  -0.0609   0.1239   1.0000
  13.500   1.4458   0.04195   0.03609  -0.0600   0.1135   1.0000
  13.750   1.4521   0.04380   0.03793  -0.0591   0.1042   1.0000
  14.000   1.4573   0.04578   0.03989  -0.0582   0.0949   1.0000
  14.250   1.4630   0.04775   0.04186  -0.0574   0.0864   1.0000
  14.500   1.4692   0.04973   0.04384  -0.0567   0.0785   1.0000
  14.750   1.4731   0.05198   0.04609  -0.0560   0.0714   1.0000
  15.000   1.4772   0.05426   0.04837  -0.0554   0.0644   1.0000
  15.250   1.4819   0.05653   0.05067  -0.0549   0.0583   1.0000
  15.500   1.4846   0.05907   0.05322  -0.0544   0.0528   1.0000
  15.750   1.4878   0.06161   0.05579  -0.0540   0.0480   1.0000
  16.000   1.4906   0.06426   0.05849  -0.0538   0.0436   1.0000
  16.250   1.4910   0.06724   0.06149  -0.0536   0.0396   1.0000
  16.500   1.4940   0.06998   0.06430  -0.0535   0.0361   1.0000
  17.000   1.4953   0.07621   0.07063  -0.0537   0.0303   1.0000
  17.250   1.4929   0.07984   0.07431  -0.0540   0.0281   1.0000
  17.500   1.4943   0.08303   0.07760  -0.0544   0.0259   1.0000
  17.750   1.4923   0.08672   0.08135  -0.0550   0.0240   1.0000
  18.000   1.4922   0.09021   0.08492  -0.0557   0.0219   1.0000
  18.250   1.4902   0.09404   0.08882  -0.0565   0.0204   1.0000
  18.500   1.4851   0.09840   0.09326  -0.0576   0.0191   1.0000
  18.750   1.4846   0.10212   0.09709  -0.0586   0.0178   1.0000
  19.000   1.4809   0.10636   0.10140  -0.0599   0.0166   1.0000
  19.250   1.4747   0.11107   0.10621  -0.0615   0.0157   1.0000
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