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EPPLER 66 AIRFOIL (e66-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 66 AIRFOIL (e66-il)
Reynolds number: 100,000
Max Cl/Cd: 64.57 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e66-il-100000.txt
Download as CSV file: xf-e66-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4147   0.10419   0.09978  -0.0318   1.0000   0.1025
  -7.750  -0.4430   0.10363   0.09935  -0.0304   1.0000   0.1028
  -7.500  -0.4645   0.10171   0.09754  -0.0325   1.0000   0.1031
  -7.250  -0.4188   0.09560   0.09134  -0.0252   1.0000   0.1076
  -7.000  -0.4284   0.09384   0.08965  -0.0228   1.0000   0.1098
  -6.750  -0.4427   0.09218   0.08808  -0.0208   1.0000   0.1120
  -6.500  -0.4601   0.08977   0.08576  -0.0234   1.0000   0.1155
  -6.250  -0.4749   0.08466   0.08070  -0.0325   1.0000   0.1180
  -6.000  -0.4690   0.08266   0.07874  -0.0256   1.0000   0.1199
  -5.750  -0.4660   0.08025   0.07634  -0.0236   1.0000   0.1230
  -5.500  -0.4634   0.07352   0.06950  -0.0372   1.0000   0.1325
  -5.250  -0.4581   0.07129   0.06733  -0.0327   1.0000   0.1344
  -5.000  -0.4501   0.06865   0.06469  -0.0317   1.0000   0.1384
  -4.750  -0.3677   0.03911   0.03276  -0.0657   1.0000   0.0619
  -4.500  -0.3374   0.03452   0.02757  -0.0687   1.0000   0.0636
  -4.250  -0.3087   0.03146   0.02407  -0.0702   1.0000   0.0651
  -4.000  -0.2806   0.02925   0.02148  -0.0710   1.0000   0.0672
  -3.750  -0.2535   0.02793   0.01973  -0.0713   1.0000   0.0738
  -3.500  -0.2261   0.02617   0.01774  -0.0718   1.0000   0.0794
  -3.250  -0.1936   0.02518   0.01652  -0.0730   0.9982   0.0911
  -3.000  -0.1515   0.02428   0.01562  -0.0760   0.9938   0.1096
  -2.750  -0.1113   0.02357   0.01489  -0.0787   0.9883   0.1455
  -2.500  -0.0687   0.02318   0.01476  -0.0821   0.9838   0.2056
  -2.250  -0.0334   0.02280   0.01466  -0.0843   0.9769   0.2716
  -2.000   0.0083   0.02266   0.01486  -0.0874   0.9720   0.3580
  -1.750   0.0396   0.02242   0.01494  -0.0886   0.9643   0.4451
  -1.500   0.0788   0.02243   0.01532  -0.0908   0.9591   0.5530
  -1.250   0.1045   0.02230   0.01549  -0.0902   0.9506   0.6504
  -1.000   0.1330   0.02230   0.01579  -0.0896   0.9441   0.7594
  -0.750   0.1506   0.02198   0.01575  -0.0865   0.9352   0.9056
  -0.500   0.1904   0.02208   0.01559  -0.0897   0.9263   1.0000
  -0.250   0.2342   0.02242   0.01567  -0.0933   0.9199   1.0000
   0.000   0.2659   0.02271   0.01577  -0.0947   0.9106   1.0000
   0.250   0.3114   0.02297   0.01585  -0.0982   0.9049   1.0000
   0.500   0.3400   0.02324   0.01599  -0.0989   0.8946   1.0000
   0.750   0.3788   0.02346   0.01609  -0.1011   0.8874   1.0000
   1.000   0.4143   0.02362   0.01617  -0.1028   0.8787   1.0000
   1.250   0.4461   0.02384   0.01631  -0.1037   0.8691   1.0000
   1.500   0.4904   0.02380   0.01622  -0.1066   0.8630   1.0000
   1.750   0.5191   0.02399   0.01638  -0.1069   0.8521   1.0000
   2.000   0.5682   0.02371   0.01608  -0.1103   0.8475   1.0000
   2.250   0.5953   0.02386   0.01623  -0.1103   0.8359   1.0000
   2.500   0.6279   0.02385   0.01623  -0.1110   0.8259   1.0000
   2.750   0.6756   0.02329   0.01571  -0.1138   0.8204   1.0000
   3.000   0.7067   0.02320   0.01567  -0.1140   0.8094   1.0000
   3.250   0.7614   0.02225   0.01479  -0.1177   0.8053   1.0000
   3.500   0.7939   0.02201   0.01461  -0.1180   0.7936   1.0000
   3.750   0.8327   0.02152   0.01423  -0.1192   0.7836   1.0000
   4.000   0.8843   0.02049   0.01329  -0.1221   0.7765   1.0000
   4.250   0.9192   0.02004   0.01293  -0.1225   0.7634   1.0000
   4.500   0.9557   0.01952   0.01252  -0.1231   0.7497   1.0000
   4.750   0.9931   0.01898   0.01206  -0.1237   0.7347   1.0000
   5.000   1.0311   0.01843   0.01161  -0.1244   0.7180   1.0000
   5.250   1.0566   0.01831   0.01156  -0.1232   0.6966   1.0000
   5.500   1.0901   0.01798   0.01126  -0.1232   0.6749   1.0000
   5.750   1.1142   0.01797   0.01130  -0.1217   0.6492   1.0000
   6.000   1.1387   0.01798   0.01135  -0.1203   0.6212   1.0000
   6.250   1.1616   0.01809   0.01144  -0.1186   0.5903   1.0000
   6.500   1.1823   0.01831   0.01161  -0.1167   0.5564   1.0000
   6.750   1.1993   0.01867   0.01192  -0.1142   0.5187   1.0000
   7.000   1.2148   0.01917   0.01231  -0.1115   0.4784   1.0000
   7.250   1.2277   0.01980   0.01283  -0.1085   0.4355   1.0000
   7.500   1.2381   0.02060   0.01345  -0.1052   0.3908   1.0000
   7.750   1.2461   0.02156   0.01420  -0.1017   0.3451   1.0000
   8.000   1.2520   0.02269   0.01510  -0.0980   0.3003   1.0000
   8.250   1.2551   0.02392   0.01609  -0.0940   0.2581   1.0000
   8.500   1.2577   0.02532   0.01724  -0.0901   0.2192   1.0000
   8.750   1.2602   0.02684   0.01853  -0.0864   0.1847   1.0000
   9.000   1.2628   0.02853   0.02003  -0.0830   0.1552   1.0000
   9.250   1.2665   0.03032   0.02168  -0.0798   0.1291   1.0000
   9.500   1.2714   0.03232   0.02358  -0.0769   0.1071   1.0000
   9.750   1.2780   0.03437   0.02552  -0.0742   0.0907   1.0000
  10.000   1.2881   0.03646   0.02757  -0.0721   0.0780   1.0000
  10.250   1.3075   0.03885   0.03002  -0.0710   0.0684   1.0000
  10.500   1.3288   0.04138   0.03252  -0.0704   0.0608   1.0000
  10.750   1.3495   0.04374   0.03512  -0.0694   0.0556   1.0000
  11.000   1.3810   0.04759   0.03906  -0.0705   0.0505   1.0000
  11.250   1.3858   0.04990   0.04178  -0.0676   0.0479   1.0000
  11.500   1.3947   0.05301   0.04524  -0.0656   0.0459   1.0000
  11.750   1.4004   0.05635   0.04890  -0.0634   0.0446   1.0000
  12.000   1.4010   0.05961   0.05243  -0.0611   0.0434   1.0000
  12.250   1.4011   0.06307   0.05607  -0.0591   0.0420   1.0000
  12.500   1.3962   0.06845   0.06169  -0.0575   0.0410   1.0000
  12.750   1.3792   0.07293   0.06648  -0.0549   0.0407   1.0000
  13.000   1.3599   0.07672   0.07058  -0.0527   0.0405   1.0000
  13.250   1.3399   0.08109   0.07524  -0.0513   0.0404   1.0000
  13.500   1.3195   0.08603   0.08046  -0.0507   0.0405   1.0000
  13.750   1.2986   0.09151   0.08619  -0.0510   0.0406   1.0000
  14.000   1.2777   0.09755   0.09245  -0.0521   0.0407   1.0000
  14.250   1.2564   0.10323   0.09839  -0.0540   0.0409   1.0000
  14.500   1.2298   0.10945   0.10490  -0.0575   0.0416   1.0000
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