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EPPLER 583 AIRFOIL (e583-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 583 AIRFOIL (e583-il)
Reynolds number: 200,000
Max Cl/Cd: 69.95 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e583-il-200000-n5.txt
Download as CSV file: xf-e583-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.0845   0.09170   0.08728  -0.1125   0.8204   0.0114
 -11.000  -0.0828   0.08788   0.08341  -0.1142   0.8110   0.0113
 -10.750  -0.0821   0.08415   0.07965  -0.1159   0.8021   0.0111
 -10.500  -0.0843   0.07986   0.07534  -0.1178   0.7948   0.0110
 -10.250  -0.0889   0.07526   0.07073  -0.1200   0.7876   0.0107
  -9.750  -0.1207   0.06057   0.05603  -0.1292   0.7750   0.0102
  -9.500  -0.1564   0.05227   0.04757  -0.1326   0.7686   0.0100
  -9.250  -0.2158   0.04338   0.03825  -0.1303   0.7625   0.0095
  -9.000  -0.2458   0.03959   0.03412  -0.1255   0.7562   0.0094
  -8.750  -0.2593   0.03623   0.03034  -0.1218   0.7512   0.0093
  -8.500  -0.2614   0.03365   0.02738  -0.1190   0.7468   0.0093
  -8.250  -0.2527   0.03233   0.02593  -0.1172   0.7419   0.0096
  -8.000  -0.2453   0.03017   0.02342  -0.1151   0.7377   0.0097
  -7.750  -0.2323   0.02858   0.02154  -0.1135   0.7341   0.0099
  -7.500  -0.2166   0.02710   0.01975  -0.1121   0.7310   0.0102
  -7.250  -0.1995   0.02568   0.01806  -0.1109   0.7272   0.0108
  -7.000  -0.1805   0.02418   0.01612  -0.1096   0.7236   0.0118
  -6.750  -0.1597   0.02315   0.01498  -0.1088   0.7201   0.0122
  -6.500  -0.1375   0.02236   0.01404  -0.1082   0.7170   0.0129
  -6.250  -0.1144   0.02133   0.01282  -0.1076   0.7142   0.0132
  -6.000  -0.0919   0.02041   0.01178  -0.1068   0.7109   0.0137
  -5.750  -0.0693   0.01962   0.01088  -0.1060   0.7078   0.0141
  -5.500  -0.0471   0.01889   0.01005  -0.1052   0.7049   0.0147
  -5.250  -0.0248   0.01829   0.00941  -0.1045   0.7021   0.0156
  -5.000  -0.0018   0.01776   0.00879  -0.1038   0.6995   0.0167
  -4.750   0.0205   0.01727   0.00823  -0.1030   0.6967   0.0182
  -4.500   0.0432   0.01689   0.00781  -0.1023   0.6936   0.0214
  -4.250   0.0662   0.01650   0.00743  -0.1017   0.6908   0.0262
  -4.000   0.0893   0.01609   0.00702  -0.1010   0.6880   0.0344
  -3.750   0.1125   0.01567   0.00665  -0.1004   0.6854   0.0515
  -3.500   0.1362   0.01527   0.00634  -0.1000   0.6831   0.0824
  -3.250   0.1584   0.01484   0.00614  -0.0994   0.6806   0.1336
  -3.000   0.1788   0.01429   0.00595  -0.0987   0.6775   0.2199
  -2.750   0.1973   0.01352   0.00574  -0.0977   0.6746   0.3635
  -2.500   0.2116   0.01259   0.00576  -0.0955   0.6718   0.5887
  -2.250   0.2316   0.01284   0.00635  -0.0929   0.6695   0.7159
  -2.000   0.2576   0.01307   0.00647  -0.0922   0.6672   0.7504
  -1.750   0.2835   0.01329   0.00658  -0.0916   0.6648   0.7725
  -1.500   0.3069   0.01354   0.00680  -0.0905   0.6618   0.7868
  -1.250   0.3304   0.01379   0.00700  -0.0893   0.6589   0.7989
  -1.000   0.3514   0.01417   0.00735  -0.0871   0.6561   0.8172
  -0.750   0.3717   0.01453   0.00768  -0.0847   0.6536   0.8336
  -0.500   0.3966   0.01465   0.00770  -0.0840   0.6514   0.8421
  -0.250   0.4232   0.01470   0.00766  -0.0838   0.6491   0.8451
   0.000   0.4469   0.01474   0.00769  -0.0832   0.6458   0.8484
   0.250   0.4725   0.01476   0.00767  -0.0831   0.6427   0.8517
   0.500   0.4998   0.01477   0.00760  -0.0834   0.6397   0.8549
   0.750   0.5268   0.01477   0.00754  -0.0835   0.6370   0.8568
   1.000   0.5546   0.01479   0.00749  -0.0837   0.6347   0.8586
   1.250   0.5802   0.01483   0.00751  -0.0835   0.6318   0.8604
   1.500   0.6037   0.01489   0.00758  -0.0830   0.6282   0.8629
   1.750   0.6295   0.01493   0.00761  -0.0829   0.6248   0.8652
   2.000   0.6570   0.01495   0.00759  -0.0832   0.6218   0.8672
   2.250   0.6859   0.01498   0.00756  -0.0838   0.6192   0.8693
   2.500   0.7136   0.01503   0.00760  -0.0842   0.6163   0.8716
   2.750   0.7352   0.01511   0.00773  -0.0832   0.6122   0.8735
   3.000   0.7598   0.01517   0.00781  -0.0829   0.6085   0.8752
   3.250   0.7863   0.01520   0.00783  -0.0830   0.6052   0.8769
   3.500   0.8147   0.01522   0.00782  -0.0834   0.6024   0.8787
   3.750   0.8375   0.01532   0.00797  -0.0828   0.5982   0.8812
   4.000   0.8608   0.01541   0.00811  -0.0823   0.5937   0.8839
   4.250   0.8875   0.01545   0.00816  -0.0825   0.5896   0.8862
   4.500   0.9159   0.01545   0.00814  -0.0829   0.5863   0.8878
   4.750   0.9347   0.01557   0.00835  -0.0815   0.5809   0.8900
   5.000   0.9568   0.01563   0.00848  -0.0807   0.5759   0.8922
   5.250   0.9827   0.01564   0.00849  -0.0806   0.5717   0.8943
   5.500   1.0037   0.01575   0.00866  -0.0797   0.5663   0.8973
   5.750   1.0247   0.01585   0.00884  -0.0788   0.5604   0.9005
   6.000   1.0503   0.01586   0.00886  -0.0787   0.5557   0.9029
   6.250   1.0665   0.01599   0.00909  -0.0769   0.5492   0.9057
   6.500   1.0859   0.01606   0.00922  -0.0756   0.5429   0.9088
   6.750   1.1066   0.01614   0.00935  -0.0746   0.5369   0.9120
   7.000   1.1217   0.01629   0.00957  -0.0727   0.5293   0.9159
   7.250   1.1400   0.01634   0.00965  -0.0712   0.5226   0.9195
   7.500   1.1516   0.01655   0.00996  -0.0685   0.5143   0.9248
   7.750   1.1689   0.01671   0.01015  -0.0670   0.5066   0.9300
   8.000   1.1817   0.01695   0.01046  -0.0648   0.4973   0.9356
   8.250   1.1958   0.01722   0.01079  -0.0628   0.4880   0.9423
   8.750   1.2273   0.01789   0.01155  -0.0600   0.4670   0.9605
   9.000   1.2461   0.01834   0.01205  -0.0596   0.4549   0.9821
   9.250   1.2602   0.01889   0.01262  -0.0583   0.4429   1.0000
   9.500   1.2730   0.01958   0.01330  -0.0570   0.4302   1.0000
   9.750   1.2840   0.02038   0.01409  -0.0555   0.4168   1.0000
  10.000   1.2935   0.02130   0.01503  -0.0539   0.4033   1.0000
  10.250   1.3013   0.02234   0.01607  -0.0522   0.3888   1.0000
  10.500   1.3073   0.02353   0.01724  -0.0505   0.3736   1.0000
  10.750   1.3118   0.02486   0.01855  -0.0486   0.3579   1.0000
  11.000   1.3160   0.02628   0.01995  -0.0469   0.3428   1.0000
  11.250   1.3190   0.02783   0.02148  -0.0452   0.3274   1.0000
  11.500   1.3217   0.02945   0.02310  -0.0436   0.3125   1.0000
  11.750   1.3243   0.03116   0.02479  -0.0421   0.2981   1.0000
  12.000   1.3255   0.03302   0.02663  -0.0406   0.2830   1.0000
  12.250   1.3269   0.03492   0.02853  -0.0392   0.2688   1.0000
  12.500   1.3281   0.03693   0.03052  -0.0379   0.2546   1.0000
  12.750   1.3292   0.03901   0.03259  -0.0368   0.2407   1.0000
  13.000   1.3297   0.04120   0.03478  -0.0357   0.2269   1.0000
  13.250   1.3302   0.04347   0.03704  -0.0348   0.2131   1.0000
  13.500   1.3301   0.04589   0.03943  -0.0339   0.1992   1.0000
  13.750   1.3299   0.04837   0.04191  -0.0332   0.1861   1.0000
  14.000   1.3293   0.05095   0.04448  -0.0325   0.1733   1.0000
  14.250   1.3290   0.05360   0.04712  -0.0320   0.1603   1.0000
  14.500   1.3292   0.05627   0.04979  -0.0316   0.1480   1.0000
  14.750   1.3295   0.05899   0.05253  -0.0313   0.1366   1.0000
  15.000   1.3294   0.06182   0.05537  -0.0311   0.1257   1.0000
  15.250   1.3287   0.06479   0.05836  -0.0310   0.1160   1.0000
  15.500   1.3273   0.06790   0.06148  -0.0311   0.1068   1.0000
  15.750   1.3279   0.07084   0.06446  -0.0312   0.0975   1.0000
  16.000   1.3271   0.07402   0.06768  -0.0314   0.0894   1.0000
  16.250   1.3252   0.07741   0.07109  -0.0317   0.0821   1.0000
  16.500   1.3246   0.08069   0.07444  -0.0321   0.0745   1.0000
  16.750   1.3229   0.08418   0.07798  -0.0327   0.0680   1.0000
  17.000   1.3195   0.08794   0.08177  -0.0334   0.0622   1.0000
  17.250   1.3186   0.09144   0.08534  -0.0341   0.0563   1.0000
  17.500   1.3151   0.09536   0.08931  -0.0350   0.0514   1.0000
  17.750   1.3128   0.09918   0.09321  -0.0361   0.0467   1.0000
  18.000   1.3098   0.10313   0.09723  -0.0372   0.0426   1.0000
  18.250   1.3060   0.10725   0.10141  -0.0385   0.0388   1.0000
  18.500   1.3029   0.11133   0.10559  -0.0399   0.0355   1.0000
  18.750   1.2988   0.11562   0.10995  -0.0414   0.0326   1.0000
  19.000   1.2954   0.11982   0.11424  -0.0430   0.0300   1.0000
  19.250   1.2916   0.12412   0.11864  -0.0448   0.0276   1.0000
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