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EPPLER 67 AIRFOIL (e67-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 67 AIRFOIL (e67-il)
Reynolds number: 1,000,000
Max Cl/Cd: 144.72 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e67-il-1000000.txt
Download as CSV file: xf-e67-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.2456   0.09724   0.09566  -0.0632   0.9915   0.0148
 -11.000  -0.5936   0.04604   0.04403  -0.0907   0.9909   0.0080
 -10.750  -0.6015   0.03452   0.03208  -0.1110   0.9842   0.0079
 -10.500  -0.5998   0.02952   0.02669  -0.1152   0.9761   0.0079
 -10.250  -0.5816   0.02578   0.02257  -0.1189   0.9734   0.0079
 -10.000  -0.5558   0.02333   0.01985  -0.1217   0.9720   0.0082
  -9.750  -0.5388   0.02162   0.01794  -0.1215   0.9668   0.0083
  -9.500  -0.5127   0.02021   0.01634  -0.1226   0.9640   0.0086
  -9.250  -0.4838   0.01883   0.01478  -0.1241   0.9624   0.0087
  -9.000  -0.4525   0.01777   0.01358  -0.1258   0.9611   0.0089
  -8.750  -0.4217   0.01649   0.01213  -0.1275   0.9598   0.0091
  -8.500  -0.3993   0.01463   0.01005  -0.1277   0.9560   0.0094
  -8.250  -0.3747   0.01360   0.00890  -0.1278   0.9515   0.0097
  -8.000  -0.3453   0.01277   0.00798  -0.1287   0.9486   0.0099
  -7.750  -0.3137   0.01205   0.00718  -0.1299   0.9462   0.0103
  -7.500  -0.2868   0.01151   0.00657  -0.1300   0.9416   0.0106
  -7.250  -0.2594   0.01102   0.00601  -0.1302   0.9367   0.0111
  -7.000  -0.2283   0.01057   0.00549  -0.1311   0.9332   0.0117
  -6.750  -0.2001   0.01020   0.00506  -0.1314   0.9283   0.0123
  -6.500  -0.1736   0.00970   0.00446  -0.1313   0.9225   0.0131
  -6.250  -0.1437   0.00924   0.00394  -0.1319   0.9181   0.0148
  -6.000  -0.1174   0.00897   0.00362  -0.1317   0.9122   0.0162
  -5.750  -0.0896   0.00861   0.00322  -0.1317   0.9066   0.0206
  -5.500  -0.0616   0.00823   0.00290  -0.1320   0.9013   0.0356
  -5.250  -0.0351   0.00799   0.00269  -0.1318   0.8951   0.0472
  -5.000  -0.0064   0.00778   0.00248  -0.1321   0.8899   0.0600
  -4.750   0.0204   0.00758   0.00232  -0.1320   0.8838   0.0746
  -4.500   0.0481   0.00739   0.00216  -0.1320   0.8779   0.0905
  -4.250   0.0758   0.00720   0.00201  -0.1321   0.8721   0.1109
  -4.000   0.1029   0.00702   0.00188  -0.1320   0.8656   0.1336
  -3.750   0.1310   0.00684   0.00175  -0.1322   0.8598   0.1615
  -3.500   0.1578   0.00665   0.00165  -0.1321   0.8531   0.1909
  -3.250   0.1857   0.00649   0.00155  -0.1322   0.8468   0.2230
  -3.000   0.2129   0.00635   0.00147  -0.1321   0.8400   0.2509
  -2.750   0.2405   0.00622   0.00140  -0.1321   0.8334   0.2827
  -2.500   0.2679   0.00608   0.00134  -0.1321   0.8265   0.3193
  -2.250   0.2954   0.00596   0.00129  -0.1321   0.8195   0.3544
  -2.000   0.3228   0.00585   0.00125  -0.1321   0.8124   0.3900
  -1.750   0.3503   0.00577   0.00122  -0.1320   0.8050   0.4233
  -1.500   0.3777   0.00569   0.00120  -0.1319   0.7973   0.4567
  -1.250   0.4051   0.00563   0.00118  -0.1319   0.7895   0.4873
  -1.000   0.4324   0.00556   0.00118  -0.1318   0.7810   0.5193
  -0.750   0.4596   0.00553   0.00118  -0.1316   0.7728   0.5501
  -0.500   0.4868   0.00549   0.00120  -0.1315   0.7638   0.5799
  -0.250   0.5139   0.00547   0.00122  -0.1313   0.7551   0.6077
   0.000   0.5408   0.00547   0.00124  -0.1311   0.7460   0.6351
   0.250   0.5678   0.00546   0.00127  -0.1309   0.7363   0.6614
   0.500   0.5946   0.00546   0.00131  -0.1307   0.7265   0.6869
   0.750   0.6210   0.00549   0.00135  -0.1303   0.7161   0.7117
   1.000   0.6474   0.00551   0.00141  -0.1300   0.7049   0.7363
   1.250   0.6736   0.00553   0.00147  -0.1296   0.6933   0.7596
   1.500   0.6995   0.00558   0.00153  -0.1291   0.6816   0.7831
   1.750   0.7250   0.00563   0.00161  -0.1286   0.6693   0.8050
   2.000   0.7502   0.00570   0.00168  -0.1280   0.6564   0.8275
   2.250   0.7747   0.00576   0.00177  -0.1272   0.6430   0.8490
   2.500   0.7989   0.00585   0.00185  -0.1264   0.6287   0.8712
   2.750   0.8220   0.00592   0.00195  -0.1252   0.6137   0.8930
   3.000   0.8440   0.00601   0.00204  -0.1239   0.5979   0.9165
   3.250   0.8638   0.00608   0.00211  -0.1220   0.5819   0.9455
   3.500   0.8929   0.00617   0.00218  -0.1223   0.5637   1.0000
   3.750   0.9179   0.00637   0.00230  -0.1218   0.5447   1.0000
   4.000   0.9428   0.00657   0.00243  -0.1213   0.5246   1.0000
   4.250   0.9670   0.00680   0.00257  -0.1207   0.5026   1.0000
   4.500   0.9908   0.00705   0.00273  -0.1200   0.4783   1.0000
   4.750   1.0140   0.00733   0.00292  -0.1192   0.4538   1.0000
   5.000   1.0364   0.00766   0.00312  -0.1182   0.4248   1.0000
   5.250   1.0585   0.00801   0.00335  -0.1172   0.3951   1.0000
   5.500   1.0804   0.00837   0.00358  -0.1162   0.3661   1.0000
   5.750   1.1009   0.00881   0.00387  -0.1149   0.3309   1.0000
   6.000   1.1205   0.00930   0.00418  -0.1135   0.2954   1.0000
   6.250   1.1396   0.00981   0.00451  -0.1121   0.2589   1.0000
   6.500   1.1579   0.01035   0.00488  -0.1105   0.2240   1.0000
   6.750   1.1764   0.01087   0.00524  -0.1089   0.1937   1.0000
   7.000   1.1938   0.01137   0.00562  -0.1071   0.1672   1.0000
   7.250   1.2103   0.01190   0.00601  -0.1051   0.1423   1.0000
   7.500   1.2276   0.01237   0.00640  -0.1033   0.1226   1.0000
   7.750   1.2441   0.01288   0.00681  -0.1014   0.1047   1.0000
   8.000   1.2608   0.01340   0.00725  -0.0996   0.0885   1.0000
   8.250   1.2771   0.01392   0.00770  -0.0976   0.0738   1.0000
   8.500   1.2925   0.01449   0.00821  -0.0956   0.0595   1.0000
   8.750   1.3078   0.01509   0.00873  -0.0937   0.0474   1.0000
   9.000   1.3226   0.01570   0.00929  -0.0916   0.0372   1.0000
   9.250   1.3369   0.01635   0.00989  -0.0895   0.0284   1.0000
   9.500   1.3500   0.01707   0.01057  -0.0873   0.0209   1.0000
   9.750   1.3642   0.01774   0.01125  -0.0853   0.0169   1.0000
  10.000   1.3779   0.01844   0.01194  -0.0833   0.0146   1.0000
  10.250   1.3909   0.01920   0.01275  -0.0811   0.0128   1.0000
  10.500   1.4058   0.01984   0.01344  -0.0794   0.0119   1.0000
  10.750   1.4189   0.02060   0.01423  -0.0775   0.0109   1.0000
  11.000   1.4283   0.02163   0.01532  -0.0751   0.0097   1.0000
  11.250   1.4406   0.02248   0.01623  -0.0732   0.0091   1.0000
  11.500   1.4535   0.02329   0.01710  -0.0715   0.0085   1.0000
  11.750   1.4652   0.02422   0.01808  -0.0697   0.0079   1.0000
  12.000   1.4746   0.02532   0.01924  -0.0677   0.0074   1.0000
  12.250   1.4765   0.02704   0.02106  -0.0649   0.0067   1.0000
  12.500   1.4846   0.02832   0.02243  -0.0631   0.0064   1.0000
  12.750   1.4933   0.02959   0.02377  -0.0613   0.0062   1.0000
  13.000   1.5025   0.03084   0.02509  -0.0598   0.0059   1.0000
  13.250   1.5093   0.03234   0.02667  -0.0582   0.0056   1.0000
  13.500   1.5150   0.03397   0.02839  -0.0566   0.0055   1.0000
  13.750   1.5218   0.03555   0.03004  -0.0552   0.0052   1.0000
  14.000   1.5256   0.03748   0.03205  -0.0538   0.0050   1.0000
  14.250   1.5273   0.03968   0.03433  -0.0524   0.0048   1.0000
  14.500   1.5240   0.04246   0.03723  -0.0511   0.0046   1.0000
  14.750   1.5144   0.04609   0.04100  -0.0498   0.0044   1.0000
  15.000   1.4988   0.05063   0.04572  -0.0488   0.0043   1.0000
  15.250   1.4976   0.05369   0.04890  -0.0484   0.0043   1.0000
  15.500   1.5004   0.05638   0.05169  -0.0483   0.0042   1.0000
  15.750   1.5036   0.05912   0.05452  -0.0484   0.0041   1.0000
  16.000   1.4998   0.06289   0.05840  -0.0487   0.0041   1.0000
  16.250   1.4959   0.06680   0.06243  -0.0492   0.0040   1.0000
  16.500   1.4946   0.07049   0.06623  -0.0500   0.0039   1.0000
  16.750   1.4890   0.07496   0.07082  -0.0511   0.0038   1.0000
  17.000   1.4815   0.07987   0.07586  -0.0525   0.0038   1.0000
  17.250   1.4734   0.08504   0.08116  -0.0542   0.0038   1.0000
  17.500   1.4648   0.09048   0.08673  -0.0562   0.0037   1.0000
  17.750   1.4538   0.09650   0.09288  -0.0587   0.0037   1.0000
  18.000   1.4430   0.10266   0.09918  -0.0614   0.0037   1.0000
  18.250   1.4315   0.10907   0.10572  -0.0644   0.0037   1.0000
  18.500   1.4193   0.11579   0.11257  -0.0677   0.0037   1.0000
  18.750   1.4071   0.12263   0.11954  -0.0713   0.0036   1.0000
  19.000   1.3946   0.12965   0.12670  -0.0751   0.0036   1.0000
  19.250   1.3825   0.13667   0.13384  -0.0791   0.0036   1.0000
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