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EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 1210 AIRFOIL (e1210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 119.45 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e1210-il-1000000.txt
Download as CSV file: xf-e1210-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1210 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
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.6874   0.08708   0.08437  -0.0517   1.0000   0.0182
 -15.000  -0.7008   0.08167   0.07891  -0.0548   1.0000   0.0183
 -14.750  -0.7239   0.07507   0.07224  -0.0590   1.0000   0.0183
 -14.500  -1.0221   0.03098   0.02741  -0.0941   1.0000   0.0168
 -14.250  -1.0289   0.02826   0.02456  -0.0935   1.0000   0.0169
 -14.000  -1.0250   0.02649   0.02268  -0.0923   1.0000   0.0171
 -13.750  -1.0168   0.02505   0.02116  -0.0909   1.0000   0.0173
 -13.500  -1.0056   0.02384   0.01987  -0.0895   1.0000   0.0175
 -13.250  -0.9923   0.02279   0.01873  -0.0881   1.0000   0.0178
 -13.000  -0.9634   0.02172   0.01758  -0.0894   0.9986   0.0182
 -12.750  -0.9272   0.02072   0.01649  -0.0919   0.9958   0.0186
 -12.500  -0.8913   0.01926   0.01495  -0.0949   0.9928   0.0193
 -12.250  -0.8592   0.01835   0.01399  -0.0964   0.9879   0.0199
 -12.000  -0.8233   0.01755   0.01314  -0.0984   0.9826   0.0207
 -11.750  -0.7943   0.01693   0.01245  -0.0988   0.9699   0.0214
 -11.500  -0.7596   0.01599   0.01145  -0.1006   0.9512   0.0224
 -11.250  -0.7014   0.01512   0.01050  -0.1069   0.9271   0.0240
 -11.000  -0.6661   0.01460   0.00975  -0.1084   0.8745   0.0253
 -10.750  -0.6435   0.01423   0.00921  -0.1073   0.8361   0.0267
 -10.500  -0.6198   0.01398   0.00879  -0.1063   0.8064   0.0280
 -10.250  -0.5964   0.01356   0.00827  -0.1054   0.7825   0.0298
 -10.000  -0.5713   0.01330   0.00790  -0.1047   0.7616   0.0315
  -9.500  -0.5202   0.01271   0.00714  -0.1034   0.7251   0.0354
  -9.250  -0.4943   0.01240   0.00678  -0.1029   0.7095   0.0373
  -9.000  -0.4678   0.01220   0.00649  -0.1023   0.6941   0.0393
  -8.500  -0.4143   0.01175   0.00591  -0.1014   0.6654   0.0434
  -8.250  -0.3874   0.01154   0.00564  -0.1009   0.6525   0.0456
  -8.000  -0.3602   0.01137   0.00541  -0.1005   0.6394   0.0479
  -7.750  -0.3327   0.01120   0.00518  -0.1001   0.6279   0.0500
  -7.500  -0.3055   0.01103   0.00496  -0.0997   0.6156   0.0523
  -7.250  -0.2774   0.01091   0.00478  -0.0993   0.6047   0.0544
  -7.000  -0.2501   0.01072   0.00455  -0.0989   0.5939   0.0568
  -6.750  -0.2220   0.01060   0.00439  -0.0986   0.5834   0.0591
  -6.500  -0.1943   0.01047   0.00420  -0.0983   0.5728   0.0615
  -6.250  -0.1662   0.01034   0.00405  -0.0980   0.5631   0.0641
  -6.000  -0.1381   0.01029   0.00392  -0.0976   0.5534   0.0664
  -5.750  -0.1100   0.01013   0.00377  -0.0974   0.5441   0.0696
  -5.500  -0.0819   0.01011   0.00368  -0.0970   0.5342   0.0724
  -5.250  -0.0536   0.00997   0.00353  -0.0968   0.5260   0.0755
  -5.000  -0.0254   0.00993   0.00344  -0.0965   0.5169   0.0783
  -4.750   0.0032   0.00986   0.00333  -0.0962   0.5092   0.0807
  -4.500   0.0312   0.00975   0.00321  -0.0959   0.5002   0.0839
  -4.250   0.0596   0.00971   0.00313  -0.0957   0.4922   0.0867
  -4.000   0.0881   0.00964   0.00302  -0.0954   0.4843   0.0894
  -3.750   0.1161   0.00959   0.00294  -0.0951   0.4760   0.0927
  -3.500   0.1449   0.00954   0.00288  -0.0949   0.4695   0.0957
  -3.250   0.1731   0.00950   0.00279  -0.0946   0.4613   0.0986
  -3.000   0.2014   0.00945   0.00273  -0.0944   0.4541   0.1022
  -2.750   0.2300   0.00942   0.00268  -0.0942   0.4472   0.1052
  -2.500   0.2582   0.00942   0.00261  -0.0939   0.4397   0.1084
  -2.250   0.2867   0.00935   0.00256  -0.0937   0.4338   0.1124
  -2.000   0.3152   0.00935   0.00253  -0.0935   0.4268   0.1159
  -1.750   0.3432   0.00937   0.00249  -0.0932   0.4191   0.1192
  -1.500   0.3718   0.00930   0.00245  -0.0930   0.4138   0.1241
  -1.250   0.4002   0.00931   0.00243  -0.0928   0.4074   0.1282
  -1.000   0.4282   0.00934   0.00241  -0.0925   0.4004   0.1323
  -0.750   0.4568   0.00929   0.00240  -0.0924   0.3952   0.1382
  -0.500   0.4850   0.00932   0.00239  -0.0921   0.3888   0.1427
  -0.250   0.5129   0.00934   0.00240  -0.0919   0.3823   0.1497
   0.000   0.5415   0.00932   0.00240  -0.0917   0.3776   0.1566
   0.250   0.5696   0.00933   0.00240  -0.0915   0.3716   0.1651
   0.500   0.5972   0.00940   0.00244  -0.0912   0.3649   0.1746
   0.750   0.6256   0.00936   0.00246  -0.0910   0.3610   0.1895
   1.000   0.6537   0.00935   0.00250  -0.0909   0.3560   0.2086
   1.250   0.6812   0.00937   0.00255  -0.0906   0.3502   0.2354
   1.500   0.7089   0.00936   0.00262  -0.0904   0.3453   0.2715
   1.750   0.7367   0.00928   0.00268  -0.0902   0.3409   0.3224
   2.000   0.7640   0.00923   0.00276  -0.0900   0.3361   0.3856
   2.250   0.7907   0.00919   0.00288  -0.0897   0.3308   0.4646
   3.000   0.8654   0.00856   0.00326  -0.0874   0.3193   0.8516
   3.250   0.9024   0.00854   0.00339  -0.0889   0.3135   1.0000
   3.500   0.9299   0.00865   0.00347  -0.0887   0.3106   1.0000
   3.750   0.9573   0.00876   0.00356  -0.0884   0.3073   1.0000
   4.000   0.9843   0.00890   0.00366  -0.0880   0.3035   1.0000
   4.250   1.0107   0.00908   0.00378  -0.0876   0.2994   1.0000
   4.500   1.0371   0.00926   0.00392  -0.0872   0.2955   1.0000
   4.750   1.0646   0.00937   0.00402  -0.0870   0.2927   1.0000
   5.000   1.0914   0.00951   0.00414  -0.0866   0.2893   1.0000
   5.250   1.1178   0.00968   0.00428  -0.0863   0.2858   1.0000
   5.500   1.1434   0.00990   0.00445  -0.0858   0.2818   1.0000
   5.750   1.1697   0.01007   0.00460  -0.0854   0.2789   1.0000
   6.000   1.1966   0.01019   0.00474  -0.0851   0.2765   1.0000
   6.250   1.2229   0.01035   0.00488  -0.0847   0.2735   1.0000
   6.500   1.2485   0.01054   0.00505  -0.0843   0.2701   1.0000
   6.750   1.2732   0.01079   0.00525  -0.0837   0.2662   1.0000
   7.000   1.2984   0.01099   0.00545  -0.0832   0.2633   1.0000
   7.250   1.3246   0.01113   0.00561  -0.0828   0.2612   1.0000
   7.500   1.3501   0.01131   0.00578  -0.0824   0.2586   1.0000
   7.750   1.3749   0.01151   0.00598  -0.0818   0.2557   1.0000
   8.000   1.3988   0.01176   0.00621  -0.0811   0.2525   1.0000
   8.250   1.4211   0.01209   0.00650  -0.0802   0.2487   1.0000
   8.500   1.4465   0.01223   0.00667  -0.0798   0.2470   1.0000
   8.750   1.4711   0.01241   0.00687  -0.0792   0.2446   1.0000
   9.000   1.4946   0.01263   0.00710  -0.0785   0.2421   1.0000
   9.250   1.5171   0.01289   0.00735  -0.0777   0.2394   1.0000
   9.500   1.5380   0.01321   0.00766  -0.0766   0.2364   1.0000
   9.750   1.5581   0.01355   0.00799  -0.0754   0.2335   1.0000
  10.000   1.5810   0.01374   0.00822  -0.0746   0.2318   1.0000
  10.250   1.6017   0.01395   0.00846  -0.0734   0.2297   1.0000
  10.500   1.6203   0.01422   0.00874  -0.0719   0.2274   1.0000
  10.750   1.6372   0.01454   0.00907  -0.0701   0.2251   1.0000
  11.000   1.6523   0.01493   0.00946  -0.0682   0.2223   1.0000
  11.250   1.6654   0.01541   0.00994  -0.0660   0.2193   1.0000
  11.500   1.6845   0.01569   0.01026  -0.0647   0.2180   1.0000
  11.750   1.7026   0.01600   0.01062  -0.0634   0.2161   1.0000
  12.000   1.7191   0.01638   0.01103  -0.0619   0.2138   1.0000
  12.250   1.7336   0.01686   0.01152  -0.0602   0.2115   1.0000
  12.500   1.7455   0.01746   0.01213  -0.0583   0.2089   1.0000
  12.750   1.7530   0.01830   0.01297  -0.0560   0.2058   1.0000
  13.000   1.7692   0.01878   0.01352  -0.0548   0.2043   1.0000
  13.250   1.7842   0.01935   0.01413  -0.0536   0.2026   1.0000
  13.500   1.7973   0.02004   0.01487  -0.0522   0.2006   1.0000
  13.750   1.8083   0.02089   0.01575  -0.0508   0.1984   1.0000
  14.000   1.8170   0.02193   0.01682  -0.0494   0.1963   1.0000
  14.250   1.8222   0.02326   0.01817  -0.0478   0.1937   1.0000
  14.500   1.8296   0.02452   0.01948  -0.0466   0.1917   1.0000
  14.750   1.8422   0.02548   0.02051  -0.0458   0.1903   1.0000
  15.000   1.8529   0.02662   0.02171  -0.0450   0.1886   1.0000
  15.250   1.8612   0.02798   0.02311  -0.0442   0.1864   1.0000
  15.500   1.8666   0.02961   0.02479  -0.0434   0.1842   1.0000
  15.750   1.8686   0.03159   0.02680  -0.0425   0.1820   1.0000
  16.000   1.8654   0.03406   0.02930  -0.0417   0.1792   1.0000
  16.250   1.8743   0.03556   0.03088  -0.0413   0.1779   1.0000
  16.500   1.8820   0.03719   0.03259  -0.0410   0.1760   1.0000
  16.750   1.8854   0.03924   0.03470  -0.0406   0.1739   1.0000
  17.000   1.8844   0.04177   0.03728  -0.0404   0.1714   1.0000
  17.250   1.8788   0.04485   0.04040  -0.0402   0.1689   1.0000
  17.500   1.8726   0.04807   0.04367  -0.0402   0.1665   1.0000
  17.750   1.8767   0.05030   0.04599  -0.0403   0.1649   1.0000
  18.000   1.8783   0.05282   0.04858  -0.0404   0.1627   1.0000
  18.250   1.8748   0.05598   0.05180  -0.0408   0.1603   1.0000
  18.500   1.8660   0.05983   0.05570  -0.0413   0.1578   1.0000
  18.750   1.8518   0.06438   0.06030  -0.0421   0.1547   1.0000
  19.000   1.8530   0.06720   0.06321  -0.0427   0.1529   1.0000
  19.250   1.8498   0.07058   0.06666  -0.0434   0.1503   1.0000
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