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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 500,000
Max Cl/Cd: 113.47 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e66-il-500000-n5.txt
Download as CSV file: xf-e66-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 66 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3750   0.10202   0.09968  -0.0471   0.9956   0.0059
 -10.250  -0.3739   0.09541   0.09309  -0.0516   0.9943   0.0060
  -9.750  -0.5181   0.03444   0.03160  -0.1114   0.9718   0.0053
  -9.500  -0.5129   0.02925   0.02594  -0.1155   0.9633   0.0054
  -9.250  -0.4893   0.02585   0.02213  -0.1192   0.9607   0.0056
  -9.000  -0.4665   0.02344   0.01938  -0.1210   0.9574   0.0058
  -8.750  -0.4449   0.02192   0.01759  -0.1214   0.9526   0.0060
  -8.500  -0.4180   0.02006   0.01543  -0.1229   0.9500   0.0061
  -8.250  -0.3899   0.01799   0.01307  -0.1247   0.9482   0.0065
  -8.000  -0.3588   0.01682   0.01173  -0.1263   0.9469   0.0068
  -7.750  -0.3335   0.01598   0.01076  -0.1264   0.9430   0.0071
  -7.500  -0.3062   0.01524   0.00990  -0.1268   0.9393   0.0075
  -7.250  -0.2753   0.01441   0.00893  -0.1279   0.9370   0.0080
  -7.000  -0.2425   0.01368   0.00806  -0.1294   0.9351   0.0085
  -6.750  -0.2085   0.01304   0.00730  -0.1310   0.9336   0.0091
  -6.500  -0.1785   0.01235   0.00654  -0.1319   0.9304   0.0101
  -6.250  -0.1505   0.01197   0.00611  -0.1321   0.9259   0.0115
  -6.000  -0.1184   0.01158   0.00562  -0.1332   0.9228   0.0131
  -5.750  -0.0845   0.01102   0.00502  -0.1347   0.9204   0.0154
  -5.500  -0.0527   0.01067   0.00459  -0.1357   0.9170   0.0177
  -5.250  -0.0242   0.01030   0.00418  -0.1360   0.9117   0.0204
  -5.000   0.0081   0.01000   0.00382  -0.1370   0.9078   0.0239
  -4.750   0.0413   0.00965   0.00347  -0.1383   0.9043   0.0300
  -4.500   0.0688   0.00938   0.00320  -0.1384   0.8980   0.0382
  -4.250   0.1001   0.00910   0.00293  -0.1392   0.8931   0.0524
  -4.000   0.1300   0.00887   0.00270  -0.1397   0.8876   0.0666
  -3.750   0.1590   0.00867   0.00251  -0.1400   0.8812   0.0813
  -3.500   0.1898   0.00847   0.00232  -0.1407   0.8757   0.0992
  -3.250   0.2174   0.00829   0.00219  -0.1408   0.8685   0.1217
  -2.750   0.2749   0.00790   0.00194  -0.1413   0.8547   0.1854
  -2.500   0.3044   0.00777   0.00183  -0.1417   0.8480   0.2120
  -2.250   0.3318   0.00764   0.00175  -0.1417   0.8400   0.2410
  -2.000   0.3605   0.00753   0.00168  -0.1419   0.8326   0.2717
  -1.750   0.3881   0.00742   0.00163  -0.1419   0.8240   0.3024
  -1.500   0.4161   0.00732   0.00158  -0.1420   0.8158   0.3410
  -1.250   0.4439   0.00722   0.00155  -0.1420   0.8068   0.3789
  -1.000   0.4713   0.00714   0.00154  -0.1419   0.7973   0.4152
  -0.750   0.4988   0.00708   0.00153  -0.1419   0.7874   0.4529
  -0.250   0.5531   0.00699   0.00155  -0.1415   0.7656   0.5283
   0.000   0.5799   0.00695   0.00159  -0.1413   0.7542   0.5669
   0.250   0.6065   0.00694   0.00163  -0.1410   0.7423   0.6039
   0.500   0.6329   0.00694   0.00168  -0.1406   0.7299   0.6403
   0.750   0.6589   0.00695   0.00174  -0.1402   0.7166   0.6761
   1.000   0.6844   0.00698   0.00181  -0.1396   0.7025   0.7122
   1.250   0.7094   0.00701   0.00189  -0.1389   0.6876   0.7477
   1.500   0.7338   0.00706   0.00198  -0.1381   0.6715   0.7831
   1.750   0.7574   0.00713   0.00207  -0.1371   0.6550   0.8173
   2.000   0.7797   0.00720   0.00218  -0.1357   0.6377   0.8516
   2.250   0.8003   0.00728   0.00227  -0.1340   0.6200   0.8882
   2.500   0.8193   0.00734   0.00233  -0.1319   0.6016   0.9333
   2.750   0.8465   0.00746   0.00239  -0.1317   0.5804   1.0000
   3.000   0.8707   0.00769   0.00253  -0.1310   0.5578   1.0000
   3.250   0.8944   0.00795   0.00268  -0.1302   0.5331   1.0000
   3.500   0.9179   0.00823   0.00285  -0.1294   0.5072   1.0000
   3.750   0.9412   0.00852   0.00304  -0.1286   0.4811   1.0000
   4.000   0.9641   0.00884   0.00324  -0.1277   0.4535   1.0000
   4.250   0.9868   0.00918   0.00347  -0.1267   0.4251   1.0000
   4.500   1.0090   0.00956   0.00371  -0.1258   0.3949   1.0000
   4.750   1.0306   0.00998   0.00399  -0.1247   0.3625   1.0000
   5.000   1.0516   0.01045   0.00431  -0.1235   0.3275   1.0000
   5.250   1.0725   0.01093   0.00463  -0.1224   0.2931   1.0000
   5.500   1.0940   0.01138   0.00496  -0.1213   0.2649   1.0000
   5.750   1.1155   0.01181   0.00530  -0.1203   0.2404   1.0000
   6.000   1.1353   0.01237   0.00571  -0.1190   0.2075   1.0000
   6.250   1.1543   0.01298   0.00614  -0.1175   0.1745   1.0000
   6.500   1.1732   0.01358   0.00659  -0.1161   0.1447   1.0000
   6.750   1.1914   0.01421   0.00707  -0.1146   0.1168   1.0000
   7.000   1.2102   0.01471   0.00750  -0.1131   0.0994   1.0000
   7.250   1.2287   0.01523   0.00796  -0.1115   0.0846   1.0000
   7.500   1.2468   0.01575   0.00846  -0.1099   0.0717   1.0000
   7.750   1.2647   0.01628   0.00896  -0.1083   0.0607   1.0000
   8.000   1.2822   0.01684   0.00949  -0.1066   0.0506   1.0000
   8.250   1.2990   0.01744   0.01006  -0.1048   0.0413   1.0000
   8.500   1.3152   0.01808   0.01067  -0.1030   0.0331   1.0000
   8.750   1.3308   0.01875   0.01133  -0.1011   0.0261   1.0000
   9.000   1.3464   0.01942   0.01203  -0.0993   0.0214   1.0000
   9.250   1.3616   0.02012   0.01275  -0.0974   0.0180   1.0000
   9.500   1.3764   0.02083   0.01349  -0.0955   0.0158   1.0000
   9.750   1.3897   0.02166   0.01435  -0.0934   0.0138   1.0000
  10.000   1.4047   0.02237   0.01514  -0.0916   0.0130   1.0000
  10.250   1.4188   0.02313   0.01599  -0.0898   0.0120   1.0000
  10.500   1.4315   0.02401   0.01691  -0.0878   0.0109   1.0000
  10.750   1.4419   0.02508   0.01806  -0.0857   0.0098   1.0000
  11.000   1.4549   0.02595   0.01901  -0.0839   0.0091   1.0000
  11.250   1.4665   0.02694   0.02010  -0.0820   0.0085   1.0000
  11.500   1.4773   0.02801   0.02126  -0.0801   0.0079   1.0000
  11.750   1.4868   0.02921   0.02253  -0.0782   0.0072   1.0000
  12.000   1.4925   0.03076   0.02416  -0.0760   0.0066   1.0000
  12.250   1.5015   0.03206   0.02556  -0.0743   0.0063   1.0000
  12.500   1.5094   0.03349   0.02711  -0.0725   0.0059   1.0000
  12.750   1.5166   0.03502   0.02874  -0.0709   0.0055   1.0000
  13.000   1.5226   0.03670   0.03054  -0.0692   0.0052   1.0000
  13.250   1.5281   0.03848   0.03241  -0.0678   0.0048   1.0000
  13.500   1.5312   0.04055   0.03458  -0.0663   0.0046   1.0000
  13.750   1.5313   0.04300   0.03715  -0.0649   0.0043   1.0000
  14.000   1.5342   0.04526   0.03954  -0.0638   0.0041   1.0000
  14.250   1.5364   0.04767   0.04208  -0.0629   0.0039   1.0000
  14.500   1.5365   0.05041   0.04496  -0.0621   0.0038   1.0000
  14.750   1.5365   0.05328   0.04795  -0.0616   0.0036   1.0000
  15.000   1.5360   0.05634   0.05114  -0.0613   0.0034   1.0000
  15.250   1.5353   0.05955   0.05447  -0.0613   0.0033   1.0000
  15.500   1.5318   0.06327   0.05833  -0.0615   0.0032   1.0000
  15.750   1.5274   0.06728   0.06248  -0.0620   0.0031   1.0000
  16.000   1.5211   0.07178   0.06712  -0.0629   0.0030   1.0000
  16.250   1.5135   0.07666   0.07214  -0.0642   0.0029   1.0000
  16.500   1.5037   0.08211   0.07775  -0.0660   0.0029   1.0000
  16.750   1.4921   0.08812   0.08393  -0.0682   0.0028   1.0000
  17.000   1.4792   0.09461   0.09058  -0.0709   0.0028   1.0000
  17.250   1.4652   0.10156   0.09769  -0.0741   0.0028   1.0000
  17.500   1.4498   0.10898   0.10528  -0.0777   0.0027   1.0000
  17.750   1.4343   0.11668   0.11315  -0.0817   0.0027   1.0000
  18.000   1.4188   0.12460   0.12122  -0.0861   0.0027   1.0000
  18.250   1.4032   0.13269   0.12947  -0.0907   0.0027   1.0000
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