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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 200,000
Max Cl/Cd: 82.55 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e67-il-200000-n5.txt
Download as CSV file: xf-e67-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 67 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4195   0.09880   0.09532  -0.0433   1.0000   0.0150
 -10.000  -0.4285   0.09402   0.09060  -0.0446   0.9995   0.0154
  -9.500  -0.5629   0.04220   0.03790  -0.0932   0.9737   0.0128
  -9.250  -0.5544   0.03841   0.03380  -0.0962   0.9670   0.0131
  -9.000  -0.5375   0.03568   0.03083  -0.0985   0.9617   0.0135
  -8.750  -0.5139   0.03312   0.02797  -0.1012   0.9587   0.0140
  -8.500  -0.5003   0.03073   0.02524  -0.1011   0.9517   0.0143
  -8.250  -0.4766   0.02820   0.02231  -0.1026   0.9481   0.0146
  -7.750  -0.4285   0.02448   0.01800  -0.1038   0.9402   0.0155
  -7.500  -0.4022   0.02297   0.01625  -0.1044   0.9365   0.0161
  -7.250  -0.3722   0.02163   0.01468  -0.1056   0.9340   0.0168
  -7.000  -0.3407   0.02032   0.01321  -0.1071   0.9322   0.0176
  -6.750  -0.3180   0.01939   0.01217  -0.1067   0.9268   0.0186
  -6.500  -0.2894   0.01867   0.01137  -0.1074   0.9231   0.0205
  -6.250  -0.2573   0.01796   0.01051  -0.1086   0.9206   0.0231
  -6.000  -0.2240   0.01700   0.00950  -0.1102   0.9187   0.0262
  -5.750  -0.1932   0.01635   0.00870  -0.1110   0.9156   0.0310
  -5.500  -0.1682   0.01573   0.00807  -0.1108   0.9100   0.0385
  -5.250  -0.1355   0.01519   0.00751  -0.1121   0.9071   0.0509
  -5.000  -0.1012   0.01464   0.00702  -0.1137   0.9048   0.0686
  -4.750  -0.0701   0.01421   0.00660  -0.1147   0.9014   0.0890
  -4.500  -0.0440   0.01385   0.00628  -0.1145   0.8956   0.1081
  -4.250  -0.0113   0.01345   0.00591  -0.1157   0.8922   0.1324
  -4.000   0.0235   0.01305   0.00555  -0.1173   0.8897   0.1595
  -3.750   0.0490   0.01278   0.00533  -0.1170   0.8834   0.1868
  -3.500   0.0801   0.01247   0.00508  -0.1178   0.8790   0.2198
  -3.250   0.1140   0.01212   0.00481  -0.1192   0.8757   0.2576
  -3.000   0.1407   0.01190   0.00467  -0.1191   0.8695   0.2940
  -2.750   0.1710   0.01164   0.00450  -0.1197   0.8644   0.3346
  -2.500   0.2047   0.01136   0.00430  -0.1210   0.8607   0.3776
  -2.250   0.2299   0.01121   0.00425  -0.1205   0.8534   0.4154
  -2.000   0.2611   0.01101   0.00412  -0.1212   0.8483   0.4569
  -1.750   0.2895   0.01086   0.00406  -0.1213   0.8421   0.4958
  -1.500   0.3180   0.01072   0.00400  -0.1213   0.8355   0.5327
  -1.250   0.3482   0.01058   0.00392  -0.1217   0.8299   0.5690
  -1.000   0.3745   0.01050   0.00392  -0.1213   0.8222   0.6027
  -0.750   0.4047   0.01040   0.00386  -0.1216   0.8163   0.6359
  -0.500   0.4300   0.01035   0.00388  -0.1209   0.8080   0.6667
  -0.250   0.4587   0.01027   0.00385  -0.1209   0.8014   0.6975
   0.000   0.4841   0.01024   0.00388  -0.1202   0.7930   0.7265
   0.250   0.5108   0.01020   0.00389  -0.1197   0.7854   0.7551
   0.500   0.5365   0.01017   0.00390  -0.1189   0.7770   0.7826
   0.750   0.5606   0.01015   0.00393  -0.1179   0.7681   0.8095
   1.250   0.6085   0.01012   0.00395  -0.1156   0.7499   0.8638
   1.500   0.6321   0.01011   0.00396  -0.1144   0.7404   0.8926
   1.750   0.6586   0.01008   0.00392  -0.1138   0.7310   0.9242
   2.000   0.6906   0.01007   0.00394  -0.1146   0.7200   0.9620
   2.250   0.7232   0.01011   0.00394  -0.1157   0.7086   1.0000
   2.500   0.7502   0.01021   0.00400  -0.1156   0.6970   1.0000
   2.750   0.7770   0.01033   0.00406  -0.1154   0.6847   1.0000
   3.000   0.8033   0.01046   0.00415  -0.1151   0.6715   1.0000
   3.250   0.8292   0.01060   0.00425  -0.1147   0.6575   1.0000
   3.500   0.8546   0.01075   0.00436  -0.1142   0.6426   1.0000
   3.750   0.8795   0.01092   0.00450  -0.1136   0.6270   1.0000
   4.000   0.9040   0.01111   0.00466  -0.1130   0.6101   1.0000
   4.250   0.9279   0.01131   0.00482  -0.1122   0.5921   1.0000
   4.500   0.9514   0.01155   0.00500  -0.1113   0.5733   1.0000
   4.750   0.9741   0.01180   0.00520  -0.1104   0.5528   1.0000
   5.000   0.9961   0.01208   0.00545  -0.1092   0.5311   1.0000
   5.250   1.0174   0.01239   0.00570  -0.1080   0.5080   1.0000
   5.500   1.0376   0.01274   0.00597  -0.1066   0.4834   1.0000
   5.750   1.0567   0.01314   0.00628  -0.1050   0.4567   1.0000
   6.000   1.0749   0.01357   0.00664  -0.1032   0.4286   1.0000
   6.250   1.0918   0.01406   0.00702  -0.1013   0.3991   1.0000
   6.500   1.1076   0.01459   0.00745  -0.0992   0.3683   1.0000
   6.750   1.1221   0.01517   0.00791  -0.0969   0.3366   1.0000
   7.000   1.1349   0.01578   0.00840  -0.0944   0.3053   1.0000
   7.250   1.1477   0.01645   0.00895  -0.0919   0.2756   1.0000
   7.500   1.1604   0.01716   0.00957  -0.0895   0.2468   1.0000
   7.750   1.1728   0.01791   0.01022  -0.0871   0.2190   1.0000
   8.000   1.1849   0.01872   0.01092  -0.0848   0.1919   1.0000
   8.250   1.1964   0.01960   0.01167  -0.0824   0.1656   1.0000
   8.500   1.2072   0.02054   0.01249  -0.0801   0.1399   1.0000
   8.750   1.2179   0.02152   0.01335  -0.0778   0.1167   1.0000
   9.000   1.2294   0.02247   0.01426  -0.0757   0.0979   1.0000
   9.250   1.2409   0.02344   0.01520  -0.0737   0.0827   1.0000
   9.500   1.2522   0.02445   0.01619  -0.0717   0.0700   1.0000
   9.750   1.2629   0.02551   0.01725  -0.0697   0.0590   1.0000
  10.000   1.2729   0.02666   0.01839  -0.0677   0.0493   1.0000
  10.250   1.2817   0.02792   0.01965  -0.0657   0.0410   1.0000
  10.500   1.2902   0.02923   0.02099  -0.0637   0.0344   1.0000
  10.750   1.2985   0.03059   0.02243  -0.0618   0.0301   1.0000
  11.000   1.3057   0.03208   0.02400  -0.0599   0.0265   1.0000
  11.250   1.3112   0.03373   0.02572  -0.0579   0.0237   1.0000
  11.500   1.3187   0.03527   0.02738  -0.0563   0.0214   1.0000
  11.750   1.3240   0.03704   0.02923  -0.0547   0.0196   1.0000
  12.000   1.3250   0.03925   0.03153  -0.0529   0.0182   1.0000
  12.250   1.3291   0.04125   0.03367  -0.0515   0.0172   1.0000
  12.500   1.3334   0.04329   0.03585  -0.0503   0.0161   1.0000
  12.750   1.3372   0.04544   0.03812  -0.0492   0.0150   1.0000
  13.000   1.3398   0.04777   0.04056  -0.0482   0.0142   1.0000
  13.250   1.3388   0.05057   0.04345  -0.0474   0.0135   1.0000
  13.500   1.3363   0.05366   0.04666  -0.0467   0.0129   1.0000
  13.750   1.3367   0.05655   0.04975  -0.0462   0.0125   1.0000
  14.000   1.3362   0.05965   0.05301  -0.0459   0.0121   1.0000
  14.250   1.3351   0.06294   0.05646  -0.0457   0.0117   1.0000
  14.500   1.3332   0.06642   0.06009  -0.0458   0.0113   1.0000
  14.750   1.3308   0.07010   0.06392  -0.0462   0.0109   1.0000
  15.000   1.3280   0.07395   0.06791  -0.0468   0.0106   1.0000
  15.250   1.3246   0.07800   0.07210  -0.0476   0.0104   1.0000
  15.500   1.3205   0.08226   0.07651  -0.0486   0.0102   1.0000
  15.750   1.3150   0.08687   0.08123  -0.0501   0.0099   1.0000
  16.000   1.3084   0.09178   0.08627  -0.0517   0.0096   1.0000
  16.250   1.3006   0.09697   0.09158  -0.0535   0.0094   1.0000
  16.500   1.2948   0.10211   0.09693  -0.0556   0.0092   1.0000
  16.750   1.2878   0.10763   0.10266  -0.0580   0.0090   1.0000
  17.000   1.2801   0.11338   0.10860  -0.0608   0.0089   1.0000
  17.250   1.2714   0.11946   0.11487  -0.0639   0.0087   1.0000
  17.500   1.2620   0.12586   0.12146  -0.0674   0.0086   1.0000
  17.750   1.2520   0.13257   0.12835  -0.0712   0.0085   1.0000
  18.000   1.2413   0.13965   0.13560  -0.0754   0.0084   1.0000
  18.250   1.2299   0.14708   0.14321  -0.0801   0.0083   1.0000
  18.500   1.2175   0.15500   0.15130  -0.0851   0.0083   1.0000
  18.750   1.2036   0.16360   0.16008  -0.0907   0.0083   1.0000
  19.000   1.1878   0.17317   0.16981  -0.0970   0.0083   1.0000
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