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EPPLER 417 AIRFOIL (e417-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 417 AIRFOIL (e417-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.87 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e417-il-1000000.txt
Download as CSV file: xf-e417-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 417 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.4667   0.07375   0.07185  -0.1032   0.9796   0.0116
 -12.000  -0.5058   0.06273   0.06061  -0.1112   0.9777   0.0115
 -11.750  -0.5252   0.05615   0.05384  -0.1163   0.9763   0.0114
 -11.500  -0.5285   0.05223   0.04981  -0.1199   0.9753   0.0116
 -11.250  -0.5333   0.04812   0.04555  -0.1235   0.9743   0.0117
 -11.000  -0.5523   0.04575   0.04308  -0.1208   0.9691   0.0117
 -10.750  -0.5606   0.04251   0.03968  -0.1215   0.9658   0.0118
 -10.500  -0.5586   0.04011   0.03714  -0.1230   0.9637   0.0121
 -10.250  -0.5567   0.03725   0.03408  -0.1245   0.9619   0.0124
  -9.000  -0.5124   0.02299   0.01823  -0.1205   0.9491   0.0110
  -8.750  -0.5172   0.02267   0.01784  -0.1147   0.9426   0.0109
  -8.500  -0.4937   0.02192   0.01700  -0.1147   0.9409   0.0108
  -8.250  -0.4683   0.02090   0.01589  -0.1150   0.9398   0.0107
  -8.000  -0.4416   0.02008   0.01500  -0.1154   0.9389   0.0106
  -7.750  -0.4174   0.01859   0.01345  -0.1152   0.9382   0.0108
  -7.500  -0.3916   0.01746   0.01227  -0.1155   0.9376   0.0108
  -7.250  -0.3638   0.01652   0.01130  -0.1163   0.9370   0.0108
  -7.000  -0.3357   0.01543   0.01016  -0.1175   0.9364   0.0110
  -6.750  -0.3061   0.01434   0.00904  -0.1193   0.9360   0.0116
  -6.500  -0.2739   0.01367   0.00834  -0.1212   0.9356   0.0121
  -6.250  -0.2749   0.01354   0.00817  -0.1158   0.9284   0.0122
  -6.000  -0.2455   0.01304   0.00764  -0.1169   0.9271   0.0128
  -5.750  -0.2140   0.01257   0.00714  -0.1183   0.9263   0.0132
  -5.500  -0.1813   0.01213   0.00666  -0.1199   0.9256   0.0136
  -5.250  -0.1480   0.01175   0.00624  -0.1215   0.9251   0.0141
  -5.000  -0.1138   0.01131   0.00576  -0.1234   0.9247   0.0154
  -4.750  -0.0791   0.01094   0.00537  -0.1253   0.9244   0.0176
  -4.500  -0.0437   0.01056   0.00501  -0.1274   0.9241   0.0261
  -4.250  -0.0014   0.00891   0.00424  -0.1328   0.9241   0.2461
  -4.000   0.0416   0.00759   0.00370  -0.1379   0.9242   0.4651
  -3.750   0.0792   0.00732   0.00357  -0.1404   0.9239   0.5217
  -3.500   0.1163   0.00719   0.00348  -0.1425   0.9235   0.5461
  -3.250   0.1528   0.00709   0.00337  -0.1445   0.9230   0.5591
  -3.000   0.1897   0.00705   0.00334  -0.1465   0.9224   0.5762
  -2.750   0.2267   0.00699   0.00326  -0.1486   0.9218   0.5854
  -2.500   0.2635   0.00694   0.00320  -0.1506   0.9210   0.5906
  -2.250   0.2747   0.00702   0.00326  -0.1470   0.9151   0.5945
  -2.000   0.3073   0.00690   0.00312  -0.1481   0.9130   0.5974
  -1.750   0.3426   0.00674   0.00297  -0.1498   0.9115   0.6001
  -1.500   0.3801   0.00658   0.00280  -0.1519   0.9099   0.6025
  -1.250   0.4180   0.00643   0.00264  -0.1542   0.9082   0.6049
  -1.000   0.4456   0.00640   0.00261  -0.1542   0.9050   0.6074
  -0.750   0.4696   0.00638   0.00259  -0.1534   0.9010   0.6097
  -0.500   0.5007   0.00633   0.00252  -0.1542   0.8983   0.6116
  -0.250   0.5345   0.00620   0.00241  -0.1556   0.8957   0.6140
   0.000   0.5680   0.00609   0.00231  -0.1569   0.8920   0.6162
   0.250   0.5894   0.00605   0.00229  -0.1555   0.8850   0.6182
   0.500   0.6216   0.00597   0.00221  -0.1564   0.8807   0.6204
   0.750   0.6473   0.00595   0.00221  -0.1560   0.8746   0.6227
   1.000   0.6748   0.00591   0.00216  -0.1559   0.8677   0.6248
   1.250   0.7010   0.00590   0.00215  -0.1556   0.8594   0.6265
   1.500   0.7308   0.00584   0.00209  -0.1561   0.8498   0.6288
   1.750   0.7562   0.00583   0.00209  -0.1555   0.8376   0.6309
   2.000   0.7822   0.00586   0.00210  -0.1551   0.8223   0.6329
   2.250   0.8057   0.00593   0.00213  -0.1542   0.8007   0.6349
   2.500   0.8269   0.00609   0.00217  -0.1527   0.7690   0.6369
   2.750   0.8410   0.00636   0.00227  -0.1496   0.7277   0.6391
   3.000   0.8452   0.00680   0.00244  -0.1445   0.6732   0.6410
   3.250   0.8504   0.00733   0.00270  -0.1397   0.6143   0.6429
   3.500   0.8570   0.00796   0.00302  -0.1354   0.5437   0.6451
   3.750   0.8697   0.00853   0.00334  -0.1325   0.4841   0.6470
   4.000   0.8848   0.00911   0.00365  -0.1301   0.4252   0.6489
   4.250   0.9013   0.00970   0.00398  -0.1281   0.3665   0.6510
   4.500   0.9203   0.01021   0.00428  -0.1266   0.3202   0.6532
   4.750   0.9384   0.01079   0.00462  -0.1250   0.2673   0.6552
   5.000   0.9566   0.01140   0.00498  -0.1234   0.2185   0.6570
   5.250   0.9748   0.01201   0.00536  -0.1219   0.1692   0.6590
   5.500   0.9926   0.01266   0.00579  -0.1203   0.1228   0.6610
   5.750   1.0097   0.01340   0.00628  -0.1186   0.0759   0.6630
   6.000   1.0240   0.01441   0.00696  -0.1164   0.0233   0.6651
   6.250   1.0441   0.01494   0.00744  -0.1151   0.0139   0.6673
   6.500   1.0653   0.01538   0.00791  -0.1140   0.0120   0.6694
   6.750   1.0869   0.01578   0.00834  -0.1130   0.0113   0.6714
   7.000   1.1077   0.01623   0.00884  -0.1119   0.0106   0.6731
   7.250   1.1282   0.01668   0.00935  -0.1108   0.0101   0.6754
   7.500   1.1472   0.01727   0.00999  -0.1094   0.0095   0.6776
   7.750   1.1633   0.01812   0.01095  -0.1074   0.0089   0.6798
   8.000   1.1818   0.01872   0.01160  -0.1060   0.0088   0.6821
   8.250   1.2001   0.01930   0.01225  -0.1045   0.0086   0.6843
   8.500   1.2174   0.01998   0.01298  -0.1029   0.0085   0.6864
   8.750   1.2340   0.02070   0.01377  -0.1012   0.0083   0.6882
   9.000   1.2501   0.02143   0.01458  -0.0995   0.0082   0.6907
   9.250   1.2648   0.02227   0.01550  -0.0976   0.0081   0.6929
   9.500   1.2797   0.02311   0.01642  -0.0957   0.0079   0.6953
   9.750   1.2933   0.02405   0.01745  -0.0937   0.0078   0.6978
  10.000   1.3067   0.02500   0.01847  -0.0918   0.0076   0.7001
  10.250   1.3191   0.02609   0.01963  -0.0897   0.0074   0.7022
  10.500   1.3315   0.02716   0.02078  -0.0878   0.0073   0.7046
  10.750   1.3433   0.02830   0.02201  -0.0858   0.0071   0.7070
  11.000   1.3542   0.02956   0.02335  -0.0837   0.0070   0.7093
  11.250   1.3638   0.03096   0.02483  -0.0816   0.0068   0.7118
  11.500   1.3727   0.03252   0.02649  -0.0795   0.0067   0.7144
  11.750   1.3804   0.03433   0.02839  -0.0774   0.0066   0.7168
  12.000   1.3883   0.03635   0.03053  -0.0754   0.0066   0.7191
  12.250   1.3954   0.03882   0.03315  -0.0735   0.0065   0.7215
  12.500   1.4009   0.04266   0.03724  -0.0716   0.0063   0.7235
  12.750   1.4022   0.04441   0.03915  -0.0692   0.0063   0.7261
  13.000   1.4038   0.04652   0.04142  -0.0671   0.0062   0.7287
  13.250   1.4036   0.04903   0.04409  -0.0651   0.0062   0.7312
  13.500   1.4013   0.05179   0.04702  -0.0632   0.0062   0.7335
  13.750   1.3964   0.05501   0.05044  -0.0615   0.0062   0.7362
  14.000   1.3895   0.05848   0.05410  -0.0600   0.0062   0.7388
  14.250   1.3799   0.06246   0.05828  -0.0588   0.0062   0.7413
  14.500   1.3697   0.06782   0.06381  -0.0581   0.0063   0.7433
  14.750   1.3582   0.07221   0.06837  -0.0578   0.0064   0.7457
  15.000   1.3482   0.07657   0.07289  -0.0581   0.0064   0.7482
  15.250   1.3386   0.08113   0.07760  -0.0590   0.0064   0.7509
  15.500   1.3222   0.08716   0.08383  -0.0607   0.0064   0.7533
  15.750   1.3119   0.09247   0.08928  -0.0627   0.0064   0.7562
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