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EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 583 AIRFOIL (e583-il)
Reynolds number: 1,000,000
Max Cl/Cd: 143.18 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e583-il-1000000.txt
Download as CSV file: xf-e583-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 583 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.0644   0.08377   0.08083  -0.1206   0.7385   0.0096
 -10.750  -0.0646   0.08012   0.07716  -0.1221   0.7329   0.0096
 -10.500  -0.0649   0.07650   0.07354  -0.1236   0.7283   0.0097
 -10.250  -0.0670   0.07253   0.06959  -0.1255   0.7237   0.0098
 -10.000  -0.0724   0.06805   0.06510  -0.1277   0.7191   0.0100
  -9.750  -0.0898   0.06043   0.05749  -0.1330   0.7148   0.0099
  -9.500  -0.1297   0.05090   0.04789  -0.1383   0.7112   0.0098
  -8.250  -0.2772   0.02413   0.01942  -0.1157   0.6924   0.0073
  -8.000  -0.2601   0.02331   0.01852  -0.1146   0.6892   0.0075
  -7.750  -0.2632   0.01749   0.01185  -0.1098   0.6863   0.0055
  -7.500  -0.2433   0.01638   0.01054  -0.1087   0.6831   0.0055
  -7.250  -0.2219   0.01543   0.00945  -0.1078   0.6806   0.0055
  -7.000  -0.1994   0.01470   0.00862  -0.1071   0.6781   0.0057
  -6.750  -0.1766   0.01403   0.00787  -0.1064   0.6754   0.0057
  -6.500  -0.1530   0.01353   0.00729  -0.1058   0.6726   0.0061
  -6.250  -0.1293   0.01307   0.00675  -0.1052   0.6700   0.0064
  -6.000  -0.1050   0.01269   0.00629  -0.1047   0.6672   0.0067
  -5.750  -0.0799   0.01239   0.00592  -0.1044   0.6649   0.0069
  -5.500  -0.0579   0.01170   0.00521  -0.1036   0.6628   0.0075
  -5.250  -0.0329   0.01136   0.00484  -0.1033   0.6604   0.0078
  -5.000  -0.0073   0.01110   0.00455  -0.1030   0.6581   0.0083
  -4.750   0.0184   0.01084   0.00426  -0.1028   0.6557   0.0087
  -4.500   0.0443   0.01062   0.00399  -0.1026   0.6533   0.0091
  -4.250   0.0696   0.01033   0.00364  -0.1023   0.6505   0.0100
  -4.000   0.0961   0.01013   0.00344  -0.1022   0.6486   0.0113
  -3.750   0.1225   0.00989   0.00320  -0.1020   0.6467   0.0146
  -3.500   0.1477   0.00951   0.00294  -0.1018   0.6445   0.0355
  -3.250   0.1739   0.00926   0.00279  -0.1017   0.6423   0.0596
  -3.000   0.2002   0.00902   0.00266  -0.1017   0.6402   0.0911
  -2.750   0.2263   0.00876   0.00254  -0.1017   0.6380   0.1384
  -2.500   0.2512   0.00832   0.00243  -0.1017   0.6356   0.2376
  -2.250   0.2754   0.00768   0.00229  -0.1017   0.6332   0.3965
  -2.000   0.2977   0.00661   0.00215  -0.1015   0.6315   0.6721
  -1.750   0.3256   0.00658   0.00223  -0.1016   0.6294   0.7265
  -1.500   0.3543   0.00661   0.00226  -0.1018   0.6272   0.7441
  -1.250   0.3832   0.00667   0.00228  -0.1020   0.6250   0.7574
  -1.000   0.4115   0.00674   0.00234  -0.1021   0.6228   0.7674
  -0.750   0.4402   0.00683   0.00238  -0.1024   0.6203   0.7755
  -0.500   0.4689   0.00696   0.00247  -0.1026   0.6175   0.7813
  -0.250   0.4974   0.00701   0.00251  -0.1029   0.6157   0.7869
   0.000   0.5255   0.00707   0.00257  -0.1029   0.6136   0.7937
   0.250   0.5527   0.00723   0.00276  -0.1027   0.6112   0.8040
   0.500   0.5797   0.00733   0.00287  -0.1025   0.6088   0.8116
   0.750   0.6075   0.00741   0.00293  -0.1025   0.6064   0.8151
   1.000   0.6360   0.00747   0.00295  -0.1029   0.6037   0.8170
   1.250   0.6649   0.00754   0.00299  -0.1033   0.6009   0.8187
   1.500   0.6934   0.00754   0.00299  -0.1037   0.5987   0.8201
   1.750   0.7219   0.00755   0.00300  -0.1040   0.5959   0.8216
   2.000   0.7504   0.00758   0.00301  -0.1044   0.5930   0.8228
   2.250   0.7785   0.00758   0.00300  -0.1047   0.5898   0.8241
   2.500   0.8064   0.00765   0.00302  -0.1049   0.5862   0.8254
   2.750   0.8340   0.00764   0.00306  -0.1051   0.5834   0.8266
   3.000   0.8616   0.00765   0.00309  -0.1053   0.5799   0.8281
   3.250   0.8890   0.00768   0.00312  -0.1054   0.5762   0.8295
   3.500   0.9162   0.00773   0.00315  -0.1056   0.5724   0.8309
   3.750   0.9435   0.00779   0.00322  -0.1057   0.5686   0.8323
   4.000   0.9710   0.00781   0.00326  -0.1059   0.5647   0.8337
   4.250   0.9981   0.00785   0.00331  -0.1060   0.5602   0.8351
   4.500   1.0243   0.00793   0.00337  -0.1060   0.5554   0.8366
   4.750   1.0515   0.00797   0.00344  -0.1062   0.5507   0.8379
   5.000   1.0782   0.00803   0.00350  -0.1062   0.5452   0.8392
   5.500   1.1294   0.00814   0.00364  -0.1059   0.5333   0.8425
   5.750   1.1538   0.00823   0.00374  -0.1055   0.5264   0.8440
   6.000   1.1787   0.00832   0.00385  -0.1052   0.5191   0.8456
   6.250   1.2018   0.00844   0.00397  -0.1046   0.5105   0.8472
   6.500   1.2256   0.00856   0.00410  -0.1041   0.5013   0.8490
   6.750   1.2472   0.00873   0.00425  -0.1032   0.4916   0.8508
   7.000   1.2687   0.00891   0.00442  -0.1023   0.4811   0.8527
   7.250   1.2887   0.00910   0.00459  -0.1011   0.4704   0.8546
   7.500   1.3055   0.00930   0.00478  -0.0993   0.4593   0.8568
   7.750   1.3200   0.00956   0.00502  -0.0970   0.4470   0.8592
   8.000   1.3339   0.00989   0.00532  -0.0947   0.4322   0.8616
   8.250   1.3481   0.01022   0.00563  -0.0925   0.4179   0.8641
   8.500   1.3623   0.01058   0.00597  -0.0903   0.4040   0.8667
   8.750   1.3743   0.01101   0.00636  -0.0879   0.3891   0.8694
   9.000   1.3857   0.01147   0.00679  -0.0854   0.3744   0.8720
   9.250   1.3936   0.01202   0.00731  -0.0823   0.3579   0.8754
   9.500   1.4011   0.01262   0.00789  -0.0793   0.3424   0.8789
   9.750   1.4069   0.01335   0.00857  -0.0762   0.3262   0.8830
  10.000   1.4105   0.01423   0.00940  -0.0730   0.3091   0.8869
  10.250   1.4129   0.01517   0.01031  -0.0697   0.2922   0.8915
  10.500   1.4144   0.01626   0.01136  -0.0665   0.2745   0.8965
  10.750   1.4165   0.01745   0.01251  -0.0636   0.2582   0.9017
  11.000   1.4171   0.01872   0.01376  -0.0607   0.2418   0.9080
  11.250   1.4179   0.02009   0.01510  -0.0580   0.2264   0.9154
  11.500   1.4188   0.02145   0.01647  -0.0554   0.2129   0.9253
  11.750   1.4161   0.02303   0.01805  -0.0524   0.1961   0.9451
  12.000   1.4209   0.02486   0.01985  -0.0516   0.1778   1.0000
  12.250   1.4273   0.02635   0.02132  -0.0504   0.1677   1.0000
  12.500   1.4264   0.02836   0.02326  -0.0486   0.1510   1.0000
  12.750   1.4230   0.03062   0.02541  -0.0467   0.1334   1.0000
  13.000   1.4268   0.03241   0.02717  -0.0455   0.1224   1.0000
  13.250   1.4275   0.03448   0.02918  -0.0441   0.1097   1.0000
  13.500   1.4266   0.03675   0.03139  -0.0428   0.0964   1.0000
  13.750   1.4256   0.03909   0.03367  -0.0416   0.0836   1.0000
  14.000   1.4275   0.04123   0.03578  -0.0406   0.0737   1.0000
  14.250   1.4292   0.04347   0.03800  -0.0398   0.0650   1.0000
  14.500   1.4342   0.04546   0.03999  -0.0391   0.0595   1.0000
  14.750   1.4354   0.04786   0.04237  -0.0385   0.0523   1.0000
  15.000   1.4370   0.05025   0.04475  -0.0379   0.0456   1.0000
  15.250   1.4399   0.05258   0.04709  -0.0374   0.0398   1.0000
  15.500   1.4425   0.05501   0.04953  -0.0371   0.0353   1.0000
  15.750   1.4445   0.05753   0.05205  -0.0368   0.0308   1.0000
  16.000   1.4465   0.06012   0.05467  -0.0366   0.0272   1.0000
  16.250   1.4497   0.06262   0.05719  -0.0365   0.0241   1.0000
  16.500   1.4504   0.06546   0.06005  -0.0365   0.0210   1.0000
  16.750   1.4521   0.06825   0.06288  -0.0366   0.0186   1.0000
  17.000   1.4547   0.07098   0.06566  -0.0368   0.0168   1.0000
  17.500   1.4576   0.07684   0.07161  -0.0374   0.0134   1.0000
  17.750   1.4577   0.08006   0.07488  -0.0379   0.0122   1.0000
  18.000   1.4598   0.08302   0.07790  -0.0384   0.0111   1.0000
  18.250   1.4591   0.08644   0.08138  -0.0390   0.0100   1.0000
  18.500   1.4596   0.08971   0.08472  -0.0398   0.0092   1.0000
  18.750   1.4595   0.09310   0.08817  -0.0406   0.0082   1.0000
  19.000   1.4577   0.09682   0.09195  -0.0416   0.0074   1.0000
  19.250   1.4575   0.10032   0.09554  -0.0426   0.0067   1.0000
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