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EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 793 AIRFOIL (e793-il)
Reynolds number: 200,000
Max Cl/Cd: 69.69 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e793-il-200000.txt
Download as CSV file: xf-e793-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 793 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2551   0.11141   0.10817  -0.0459   1.0000   0.0799
 -11.000  -0.5014   0.06877   0.06500  -0.0708   1.0000   0.0431
 -10.750  -0.5244   0.06354   0.05976  -0.0726   1.0000   0.0426
 -10.500  -0.5564   0.05870   0.05489  -0.0741   1.0000   0.0421
 -10.250  -0.5920   0.05559   0.05177  -0.0729   1.0000   0.0419
 -10.000  -0.6294   0.05405   0.05025  -0.0694   1.0000   0.0417
  -9.750  -0.6550   0.05104   0.04710  -0.0688   0.9990   0.0414
  -9.500  -0.6424   0.04321   0.03865  -0.0786   0.9891   0.0402
  -9.250  -0.6185   0.03772   0.03254  -0.0848   0.9823   0.0397
  -9.000  -0.5912   0.03438   0.02879  -0.0881   0.9744   0.0399
  -8.750  -0.5574   0.03193   0.02600  -0.0914   0.9689   0.0410
  -8.500  -0.5249   0.02977   0.02351  -0.0938   0.9616   0.0418
  -8.250  -0.4856   0.02765   0.02108  -0.0970   0.9580   0.0425
  -8.000  -0.4555   0.02608   0.01927  -0.0981   0.9490   0.0431
  -7.750  -0.4164   0.02414   0.01722  -0.1007   0.9453   0.0442
  -7.500  -0.3853   0.02279   0.01591  -0.1017   0.9370   0.0455
  -7.250  -0.3459   0.02160   0.01470  -0.1042   0.9323   0.0476
  -7.000  -0.3022   0.02053   0.01350  -0.1074   0.9294   0.0505
  -6.750  -0.2727   0.01924   0.01228  -0.1081   0.9197   0.0532
  -6.500  -0.2301   0.01814   0.01116  -0.1112   0.9154   0.0576
  -6.250  -0.1967   0.01703   0.01007  -0.1126   0.9061   0.0635
  -6.000  -0.1568   0.01575   0.00885  -0.1154   0.8993   0.0823
  -5.750  -0.1248   0.01438   0.00782  -0.1170   0.8881   0.1417
  -5.500  -0.0862   0.01365   0.00723  -0.1193   0.8793   0.1969
  -5.250  -0.0537   0.01329   0.00692  -0.1202   0.8666   0.2334
  -5.000  -0.0222   0.01310   0.00671  -0.1208   0.8530   0.2641
  -4.750   0.0094   0.01304   0.00656  -0.1212   0.8395   0.2932
  -4.500   0.0400   0.01301   0.00650  -0.1215   0.8262   0.3179
  -4.250   0.0704   0.01302   0.00639  -0.1217   0.8129   0.3385
  -4.000   0.0979   0.01301   0.00631  -0.1214   0.7982   0.3552
  -3.750   0.1252   0.01299   0.00622  -0.1210   0.7838   0.3701
  -3.500   0.1528   0.01298   0.00613  -0.1207   0.7699   0.3849
  -3.250   0.1807   0.01298   0.00603  -0.1204   0.7567   0.3993
  -3.000   0.2090   0.01300   0.00590  -0.1202   0.7441   0.4134
  -2.750   0.2356   0.01298   0.00585  -0.1197   0.7305   0.4256
  -2.500   0.2624   0.01296   0.00579  -0.1192   0.7174   0.4376
  -2.250   0.2899   0.01296   0.00569  -0.1190   0.7052   0.4503
  -1.750   0.3441   0.01297   0.00559  -0.1182   0.6811   0.4743
  -1.500   0.3712   0.01298   0.00554  -0.1179   0.6695   0.4867
  -1.250   0.3992   0.01304   0.00548  -0.1177   0.6591   0.5001
  -1.000   0.4254   0.01303   0.00549  -0.1172   0.6473   0.5121
  -0.750   0.4524   0.01306   0.00549  -0.1169   0.6369   0.5250
  -0.500   0.4800   0.01312   0.00547  -0.1166   0.6271   0.5390
  -0.250   0.5066   0.01316   0.00550  -0.1163   0.6162   0.5537
   0.000   0.5339   0.01323   0.00553  -0.1160   0.6072   0.5683
   0.250   0.5602   0.01326   0.00559  -0.1155   0.5972   0.5834
   0.500   0.5872   0.01334   0.00565  -0.1152   0.5883   0.5995
   0.750   0.6137   0.01339   0.00572  -0.1148   0.5790   0.6166
   1.000   0.6403   0.01348   0.00582  -0.1144   0.5705   0.6347
   1.250   0.6668   0.01355   0.00590  -0.1140   0.5619   0.6540
   1.500   0.6932   0.01366   0.00602  -0.1136   0.5537   0.6748
   1.750   0.7188   0.01372   0.00613  -0.1130   0.5454   0.6953
   2.000   0.7446   0.01382   0.00627  -0.1124   0.5380   0.7178
   2.250   0.7697   0.01390   0.00640  -0.1117   0.5299   0.7434
   2.500   0.7945   0.01400   0.00654  -0.1108   0.5230   0.7693
   2.750   0.8171   0.01404   0.00670  -0.1096   0.5151   0.7993
   3.000   0.8397   0.01412   0.00679  -0.1082   0.5089   0.8347
   3.250   0.8577   0.01411   0.00693  -0.1058   0.5017   0.8819
   3.500   0.8881   0.01404   0.00690  -0.1060   0.4944   1.0000
   3.750   0.9179   0.01433   0.00710  -0.1067   0.4875   1.0000
   4.000   0.9459   0.01456   0.00729  -0.1070   0.4803   1.0000
   4.250   0.9753   0.01488   0.00746  -0.1074   0.4743   1.0000
   4.500   1.0007   0.01510   0.00774  -0.1071   0.4668   1.0000
   4.750   1.0283   0.01536   0.00792  -0.1071   0.4606   1.0000
   5.000   1.0551   0.01568   0.00822  -0.1071   0.4544   1.0000
   5.250   1.0809   0.01594   0.00849  -0.1068   0.4476   1.0000
   5.500   1.1090   0.01627   0.00870  -0.1069   0.4419   1.0000
   5.750   1.1332   0.01656   0.00907  -0.1063   0.4353   1.0000
   6.000   1.1592   0.01684   0.00934  -0.1061   0.4292   1.0000
   6.250   1.1863   0.01721   0.00964  -0.1061   0.4236   1.0000
   6.500   1.2096   0.01749   0.01002  -0.1053   0.4170   1.0000
   6.750   1.2357   0.01780   0.01029  -0.1051   0.4112   1.0000
   7.000   1.2605   0.01817   0.01068  -0.1047   0.4053   1.0000
   7.250   1.2837   0.01847   0.01103  -0.1040   0.3987   1.0000
   7.500   1.3102   0.01880   0.01130  -0.1038   0.3931   1.0000
   7.750   1.3317   0.01915   0.01176  -0.1028   0.3866   1.0000
   8.000   1.3550   0.01945   0.01207  -0.1021   0.3803   1.0000
   8.250   1.3803   0.01985   0.01243  -0.1018   0.3746   1.0000
   8.500   1.3997   0.02017   0.01289  -0.1005   0.3678   1.0000
   8.750   1.4232   0.02049   0.01317  -0.0999   0.3618   1.0000
   9.000   1.4436   0.02090   0.01366  -0.0988   0.3554   1.0000
   9.250   1.4634   0.02122   0.01404  -0.0975   0.3487   1.0000
   9.500   1.4869   0.02163   0.01440  -0.0969   0.3428   1.0000
   9.750   1.5020   0.02200   0.01493  -0.0949   0.3359   1.0000
  10.000   1.5224   0.02237   0.01528  -0.0939   0.3297   1.0000
  10.250   1.5385   0.02284   0.01585  -0.0921   0.3232   1.0000
  10.500   1.5534   0.02322   0.01630  -0.0902   0.3164   1.0000
  10.750   1.5703   0.02369   0.01676  -0.0886   0.3101   1.0000
  11.250   1.5938   0.02463   0.01779  -0.0838   0.2969   1.0000
  11.500   1.5988   0.02524   0.01857  -0.0805   0.2901   1.0000
  11.750   1.6082   0.02582   0.01918  -0.0780   0.2833   1.0000
  12.000   1.6150   0.02658   0.02002  -0.0753   0.2762   1.0000
  12.250   1.6206   0.02736   0.02087  -0.0727   0.2690   1.0000
  12.500   1.6262   0.02829   0.02187  -0.0702   0.2617   1.0000
  12.750   1.6292   0.02934   0.02300  -0.0677   0.2540   1.0000
  13.000   1.6326   0.03055   0.02427  -0.0654   0.2465   1.0000
  13.250   1.6336   0.03194   0.02572  -0.0632   0.2384   1.0000
  13.500   1.6342   0.03353   0.02739  -0.0612   0.2304   1.0000
  13.750   1.6335   0.03529   0.02917  -0.0594   0.2223   1.0000
  14.000   1.6316   0.03734   0.03133  -0.0578   0.2137   1.0000
  14.250   1.6290   0.03954   0.03350  -0.0564   0.2059   1.0000
  14.500   1.6249   0.04208   0.03620  -0.0553   0.1971   1.0000
  14.750   1.6201   0.04480   0.03892  -0.0544   0.1894   1.0000
  15.000   1.6141   0.04782   0.04202  -0.0538   0.1811   1.0000
  15.250   1.6078   0.05102   0.04527  -0.0534   0.1735   1.0000
  15.500   1.6004   0.05452   0.04880  -0.0532   0.1660   1.0000
  15.750   1.5934   0.05812   0.05246  -0.0532   0.1588   1.0000
  16.000   1.5853   0.06197   0.05633  -0.0535   0.1520   1.0000
  16.250   1.5780   0.06590   0.06033  -0.0539   0.1454   1.0000
  16.500   1.5699   0.07001   0.06448  -0.0546   0.1391   1.0000
  16.750   1.5629   0.07409   0.06860  -0.0553   0.1332   1.0000
  17.000   1.5553   0.07842   0.07302  -0.0563   0.1274   1.0000
  17.250   1.5502   0.08232   0.07687  -0.0570   0.1220   1.0000
  17.500   1.5423   0.08694   0.08165  -0.0584   0.1168   1.0000
  17.750   1.5369   0.09103   0.08570  -0.0595   0.1118   1.0000
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