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EPPLER 582 AIRFOIL (e582-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 582 AIRFOIL (e582-il)
Reynolds number: 200,000
Max Cl/Cd: 74.99 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e582-il-200000-n5.txt
Download as CSV file: xf-e582-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 582 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.1816   0.11201   0.10836  -0.0808   0.9526   0.0202
 -11.000  -0.1697   0.10757   0.10391  -0.0847   0.9468   0.0205
 -10.500  -0.1548   0.09425   0.09054  -0.0950   0.9344   0.0116
 -10.250  -0.1407   0.08984   0.08610  -0.0996   0.9281   0.0113
 -10.000  -0.1263   0.08556   0.08179  -0.1044   0.9204   0.0110
  -9.750  -0.1174   0.07946   0.07567  -0.1106   0.9122   0.0110
  -9.500  -0.1067   0.07431   0.07048  -0.1163   0.9028   0.0105
  -9.250  -0.1040   0.06782   0.06396  -0.1228   0.8911   0.0105
  -9.000  -0.1085   0.06037   0.05646  -0.1307   0.8780   0.0100
  -8.750  -0.1237   0.05405   0.04999  -0.1350   0.8645   0.0100
  -8.500  -0.1453   0.04913   0.04487  -0.1349   0.8526   0.0096
  -8.250  -0.1653   0.04443   0.03991  -0.1329   0.8424   0.0094
  -8.000  -0.1763   0.04009   0.03525  -0.1306   0.8343   0.0094
  -7.750  -0.1764   0.03707   0.03193  -0.1287   0.8274   0.0096
  -7.500  -0.1704   0.03451   0.02907  -0.1271   0.8219   0.0099
  -7.250  -0.1644   0.03171   0.02590  -0.1251   0.8158   0.0101
  -7.000  -0.1530   0.02911   0.02285  -0.1234   0.8109   0.0108
  -6.750  -0.1390   0.02649   0.01967  -0.1217   0.8064   0.0114
  -6.500  -0.1217   0.02457   0.01736  -0.1203   0.8014   0.0115
  -6.250  -0.1008   0.02288   0.01531  -0.1193   0.7973   0.0116
  -6.000  -0.0770   0.02144   0.01353  -0.1187   0.7939   0.0117
  -5.750  -0.0549   0.02024   0.01220  -0.1179   0.7897   0.0119
  -5.500  -0.0323   0.01929   0.01116  -0.1172   0.7854   0.0123
  -5.250  -0.0084   0.01850   0.01026  -0.1167   0.7817   0.0127
  -5.000   0.0163   0.01776   0.00940  -0.1163   0.7786   0.0132
  -4.750   0.0388   0.01712   0.00869  -0.1155   0.7745   0.0140
  -4.500   0.0616   0.01655   0.00802  -0.1147   0.7703   0.0151
  -4.250   0.0854   0.01603   0.00745  -0.1142   0.7668   0.0165
  -4.000   0.1109   0.01561   0.00696  -0.1140   0.7637   0.0204
  -3.750   0.1348   0.01519   0.00653  -0.1135   0.7601   0.0267
  -3.500   0.1578   0.01473   0.00615  -0.1129   0.7559   0.0429
  -3.250   0.1820   0.01428   0.00584  -0.1126   0.7523   0.0798
  -3.000   0.2063   0.01372   0.00556  -0.1125   0.7492   0.1557
  -2.750   0.2290   0.01297   0.00533  -0.1123   0.7460   0.2945
  -2.500   0.2476   0.01199   0.00520  -0.1115   0.7418   0.5105
  -2.250   0.2601   0.01208   0.00605  -0.1070   0.7380   0.7103
  -2.000   0.2875   0.01232   0.00614  -0.1067   0.7348   0.7571
  -1.500   0.3365   0.01282   0.00646  -0.1047   0.7278   0.7942
  -1.250   0.3594   0.01303   0.00660  -0.1033   0.7239   0.8065
  -1.000   0.3797   0.01334   0.00686  -0.1010   0.7203   0.8236
  -0.750   0.3991   0.01362   0.00709  -0.0983   0.7174   0.8409
  -0.500   0.4184   0.01376   0.00720  -0.0962   0.7133   0.8507
  -0.250   0.4427   0.01379   0.00717  -0.0957   0.7091   0.8547
   0.000   0.4704   0.01378   0.00708  -0.0959   0.7054   0.8579
   0.250   0.5008   0.01377   0.00695  -0.0968   0.7023   0.8606
   0.500   0.5246   0.01378   0.00694  -0.0961   0.6981   0.8625
   0.750   0.5491   0.01380   0.00693  -0.0957   0.6935   0.8643
   1.000   0.5763   0.01379   0.00688  -0.0958   0.6896   0.8660
   1.250   0.6057   0.01378   0.00679  -0.0963   0.6864   0.8677
   1.500   0.6295   0.01383   0.00685  -0.0959   0.6812   0.8695
   1.750   0.6560   0.01385   0.00685  -0.0959   0.6765   0.8714
   2.000   0.6853   0.01384   0.00679  -0.0965   0.6725   0.8729
   2.250   0.7118   0.01388   0.00683  -0.0967   0.6674   0.8743
   2.500   0.7377   0.01391   0.00687  -0.0967   0.6618   0.8758
   2.750   0.7649   0.01390   0.00684  -0.0967   0.6574   0.8770
   3.000   0.7892   0.01394   0.00690  -0.0963   0.6519   0.8782
   3.250   0.8141   0.01398   0.00696  -0.0960   0.6462   0.8794
   3.500   0.8426   0.01397   0.00693  -0.0964   0.6414   0.8804
   3.750   0.8649   0.01405   0.00707  -0.0956   0.6345   0.8820
   4.000   0.8911   0.01406   0.00709  -0.0956   0.6283   0.8836
   4.250   0.9156   0.01413   0.00718  -0.0952   0.6214   0.8852
   4.500   0.9410   0.01417   0.00726  -0.0951   0.6142   0.8865
   4.750   0.9659   0.01425   0.00736  -0.0949   0.6069   0.8879
   5.000   0.9912   0.01432   0.00745  -0.0947   0.5991   0.8892
   5.250   1.0147   0.01441   0.00760  -0.0942   0.5906   0.8905
   5.500   1.0382   0.01447   0.00767  -0.0936   0.5823   0.8918
   5.750   1.0578   0.01458   0.00785  -0.0923   0.5726   0.8936
   6.000   1.0789   0.01469   0.00799  -0.0913   0.5628   0.8955
   6.250   1.0999   0.01481   0.00813  -0.0903   0.5522   0.8974
   6.500   1.1182   0.01498   0.00834  -0.0888   0.5402   0.8994
   6.750   1.1358   0.01515   0.00855  -0.0872   0.5276   0.9015
   7.000   1.1534   0.01538   0.00880  -0.0856   0.5143   0.9036
   7.250   1.1693   0.01565   0.00909  -0.0838   0.4998   0.9058
   7.500   1.1835   0.01596   0.00940  -0.0816   0.4844   0.9082
   7.750   1.1971   0.01633   0.00978  -0.0795   0.4680   0.9110
   8.000   1.2097   0.01678   0.01022  -0.0772   0.4509   0.9142
   8.250   1.2209   0.01732   0.01073  -0.0749   0.4327   0.9181
   8.500   1.2299   0.01790   0.01130  -0.0722   0.4142   0.9221
   8.750   1.2380   0.01857   0.01196  -0.0695   0.3949   0.9265
   9.000   1.2454   0.01936   0.01272  -0.0670   0.3757   0.9317
   9.250   1.2512   0.02024   0.01359  -0.0642   0.3570   0.9380
   9.750   1.2664   0.02219   0.01554  -0.0601   0.3192   0.9618
  10.000   1.2730   0.02331   0.01664  -0.0583   0.3009   1.0000
  10.250   1.2793   0.02469   0.01797  -0.0566   0.2822   1.0000
  10.500   1.2868   0.02606   0.01933  -0.0552   0.2640   1.0000
  10.750   1.2929   0.02755   0.02080  -0.0538   0.2455   1.0000
  11.000   1.2985   0.02914   0.02235  -0.0523   0.2279   1.0000
  11.250   1.3031   0.03084   0.02401  -0.0509   0.2105   1.0000
  11.500   1.3075   0.03259   0.02573  -0.0496   0.1943   1.0000
  11.750   1.3126   0.03436   0.02749  -0.0485   0.1783   1.0000
  12.000   1.3170   0.03624   0.02934  -0.0473   0.1624   1.0000
  12.250   1.3213   0.03818   0.03128  -0.0463   0.1477   1.0000
  12.500   1.3252   0.04020   0.03329  -0.0453   0.1336   1.0000
  12.750   1.3292   0.04228   0.03536  -0.0445   0.1211   1.0000
  13.000   1.3325   0.04447   0.03756  -0.0437   0.1088   1.0000
  13.250   1.3355   0.04675   0.03984  -0.0429   0.0977   1.0000
  13.750   1.3411   0.05154   0.04467  -0.0418   0.0771   1.0000
  14.000   1.3435   0.05407   0.04723  -0.0414   0.0681   1.0000
  14.250   1.3450   0.05677   0.04997  -0.0410   0.0603   1.0000
  14.500   1.3450   0.05970   0.05292  -0.0408   0.0530   1.0000
  14.750   1.3467   0.06251   0.05580  -0.0406   0.0464   1.0000
  15.000   1.3469   0.06558   0.05892  -0.0406   0.0411   1.0000
  15.250   1.3458   0.06886   0.06226  -0.0407   0.0364   1.0000
  15.500   1.3462   0.07206   0.06556  -0.0410   0.0324   1.0000
  15.750   1.3439   0.07568   0.06923  -0.0414   0.0290   1.0000
  16.000   1.3430   0.07918   0.07285  -0.0419   0.0260   1.0000
  16.250   1.3405   0.08299   0.07674  -0.0425   0.0235   1.0000
  16.500   1.3372   0.08698   0.08086  -0.0434   0.0212   1.0000
  16.750   1.3348   0.09096   0.08495  -0.0443   0.0191   1.0000
  17.000   1.3293   0.09545   0.08951  -0.0456   0.0174   1.0000
  17.250   1.3268   0.09957   0.09379  -0.0468   0.0158   1.0000
  17.500   1.3221   0.10410   0.09843  -0.0484   0.0144   1.0000
  17.750   1.3153   0.10907   0.10350  -0.0502   0.0134   1.0000
  18.000   1.3109   0.11371   0.10831  -0.0520   0.0123   1.0000
  18.250   1.3053   0.11863   0.11335  -0.0540   0.0114   1.0000
  18.500   1.2979   0.12393   0.11877  -0.0564   0.0107   1.0000
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