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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 100,000
Max Cl/Cd: 52.18 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e561-il-100000-n5.txt
Download as CSV file: xf-e561-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 561 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.4001   0.10373   0.09833  -0.0580   1.0000   0.0343
 -12.500  -0.4621   0.08811   0.08252  -0.0656   1.0000   0.0339
 -12.250  -0.4911   0.08044   0.07472  -0.0690   1.0000   0.0337
 -12.000  -0.5143   0.07455   0.06874  -0.0712   1.0000   0.0337
 -11.750  -0.5324   0.06997   0.06408  -0.0724   1.0000   0.0338
 -11.500  -0.5490   0.06606   0.06011  -0.0730   1.0000   0.0339
 -11.250  -0.5660   0.06260   0.05660  -0.0729   1.0000   0.0341
 -11.000  -0.5822   0.05979   0.05377  -0.0720   1.0000   0.0342
 -10.750  -0.5987   0.05697   0.05092  -0.0714   0.9993   0.0343
 -10.500  -0.5834   0.05324   0.04702  -0.0770   0.9919   0.0351
 -10.250  -0.5659   0.05040   0.04418  -0.0815   0.9837   0.0359
 -10.000  -0.5542   0.04729   0.04100  -0.0858   0.9725   0.0367
  -9.750  -0.5419   0.04383   0.03743  -0.0906   0.9599   0.0379
  -9.500  -0.5251   0.04034   0.03378  -0.0960   0.9472   0.0392
  -9.250  -0.5056   0.03686   0.03014  -0.1017   0.9345   0.0411
  -9.000  -0.4847   0.03414   0.02731  -0.1058   0.9227   0.0434
  -8.750  -0.4584   0.03176   0.02478  -0.1097   0.9134   0.0475
  -8.500  -0.4299   0.02955   0.02244  -0.1133   0.9044   0.0531
  -8.250  -0.4024   0.02753   0.02033  -0.1162   0.8945   0.0612
  -8.000  -0.3682   0.02556   0.01834  -0.1200   0.8872   0.0744
  -7.750  -0.3372   0.02419   0.01690  -0.1224   0.8771   0.0926
  -7.500  -0.2983   0.02302   0.01568  -0.1257   0.8700   0.1138
  -7.250  -0.2646   0.02225   0.01488  -0.1278   0.8596   0.1343
  -7.000  -0.2229   0.02164   0.01416  -0.1311   0.8520   0.1601
  -6.750  -0.1895   0.02132   0.01378  -0.1326   0.8405   0.1781
  -6.500  -0.1499   0.02090   0.01319  -0.1350   0.8316   0.1927
  -6.250  -0.1153   0.02054   0.01262  -0.1365   0.8199   0.2057
  -6.000  -0.0812   0.02032   0.01234  -0.1377   0.8086   0.2167
  -5.750  -0.0433   0.02003   0.01189  -0.1396   0.7985   0.2279
  -5.500  -0.0126   0.01977   0.01143  -0.1402   0.7855   0.2390
  -5.250   0.0194   0.01963   0.01122  -0.1409   0.7740   0.2479
  -5.000   0.0538   0.01939   0.01079  -0.1421   0.7633   0.2580
  -4.750   0.0826   0.01928   0.01058  -0.1422   0.7508   0.2669
  -4.500   0.1135   0.01911   0.01028  -0.1428   0.7397   0.2758
  -4.250   0.1445   0.01900   0.01002  -0.1433   0.7289   0.2850
  -4.000   0.1725   0.01890   0.00982  -0.1433   0.7174   0.2933
  -3.750   0.2029   0.01882   0.00960  -0.1436   0.7075   0.3023
  -3.500   0.2309   0.01874   0.00943  -0.1436   0.6966   0.3105
  -3.250   0.2595   0.01869   0.00928  -0.1437   0.6867   0.3191
  -3.000   0.2883   0.01863   0.00909  -0.1437   0.6769   0.3275
  -2.750   0.3157   0.01861   0.00901  -0.1436   0.6672   0.3359
  -2.500   0.3447   0.01857   0.00882  -0.1437   0.6585   0.3445
  -2.250   0.3716   0.01857   0.00879  -0.1435   0.6490   0.3526
  -2.000   0.4004   0.01855   0.00863  -0.1436   0.6406   0.3618
  -1.750   0.4269   0.01857   0.00864  -0.1433   0.6316   0.3695
  -1.500   0.4555   0.01858   0.00851  -0.1433   0.6238   0.3792
  -1.250   0.4822   0.01862   0.00855  -0.1430   0.6157   0.3870
  -1.000   0.5100   0.01866   0.00847  -0.1430   0.6078   0.3970
  -0.750   0.5371   0.01870   0.00850  -0.1428   0.6005   0.4050
  -0.500   0.5640   0.01877   0.00850  -0.1426   0.5926   0.4152
  -0.250   0.5922   0.01882   0.00851  -0.1425   0.5865   0.4236
   0.000   0.6181   0.01892   0.00859  -0.1422   0.5787   0.4340
   0.250   0.6448   0.01898   0.00866  -0.1419   0.5720   0.4429
   0.500   0.6720   0.01909   0.00870  -0.1417   0.5657   0.4534
   0.750   0.6976   0.01919   0.00885  -0.1413   0.5587   0.4633
   1.000   0.7252   0.01930   0.00891  -0.1412   0.5531   0.4741
   1.250   0.7514   0.01944   0.00906  -0.1409   0.5469   0.4856
   1.500   0.7770   0.01957   0.00923  -0.1405   0.5405   0.4968
   1.750   0.8045   0.01969   0.00932  -0.1404   0.5353   0.5095
   2.000   0.8299   0.01986   0.00953  -0.1399   0.5295   0.5228
   2.250   0.8552   0.02002   0.00976  -0.1395   0.5237   0.5364
   2.500   0.8822   0.02017   0.00990  -0.1393   0.5186   0.5516
   2.750   0.9078   0.02036   0.01013  -0.1389   0.5133   0.5683
   3.000   0.9322   0.02056   0.01043  -0.1383   0.5076   0.5869
   3.250   0.9582   0.02072   0.01064  -0.1379   0.5028   0.6082
   3.500   0.9849   0.02090   0.01083  -0.1376   0.4985   0.6333
   3.750   1.0065   0.02111   0.01124  -0.1365   0.4927   0.6616
   4.000   1.0296   0.02127   0.01153  -0.1355   0.4877   0.6970
   4.250   1.0529   0.02137   0.01173  -0.1345   0.4837   0.7433
   4.750   1.0868   0.02147   0.01224  -0.1298   0.4740   1.0000
   5.000   1.1136   0.02182   0.01253  -0.1299   0.4693   1.0000
   5.250   1.1424   0.02214   0.01275  -0.1302   0.4654   1.0000
   5.500   1.1643   0.02261   0.01328  -0.1294   0.4603   1.0000
   5.750   1.1876   0.02303   0.01371  -0.1289   0.4552   1.0000
   6.000   1.2136   0.02339   0.01404  -0.1287   0.4509   1.0000
   6.250   1.2404   0.02377   0.01437  -0.1287   0.4470   1.0000
   6.500   1.2589   0.02431   0.01502  -0.1274   0.4417   1.0000
   6.750   1.2814   0.02475   0.01550  -0.1267   0.4369   1.0000
   7.000   1.3073   0.02511   0.01583  -0.1265   0.4329   1.0000
   7.250   1.3292   0.02561   0.01636  -0.1257   0.4286   1.0000
   7.500   1.3462   0.02620   0.01707  -0.1242   0.4234   1.0000
   7.750   1.3679   0.02665   0.01755  -0.1233   0.4188   1.0000
   8.000   1.3943   0.02701   0.01788  -0.1232   0.4150   1.0000
   8.250   1.4088   0.02768   0.01868  -0.1214   0.4101   1.0000
   8.500   1.4239   0.02831   0.01942  -0.1196   0.4049   1.0000
   8.750   1.4454   0.02875   0.01988  -0.1187   0.4006   1.0000
   9.000   1.4696   0.02916   0.02028  -0.1183   0.3966   1.0000
   9.250   1.4727   0.03003   0.02136  -0.1148   0.3912   1.0000
   9.500   1.4863   0.03066   0.02207  -0.1128   0.3863   1.0000
   9.750   1.5090   0.03104   0.02244  -0.1122   0.3821   1.0000
  10.000   1.5158   0.03191   0.02345  -0.1094   0.3772   1.0000
  10.250   1.5203   0.03288   0.02457  -0.1064   0.3719   1.0000
  10.500   1.5368   0.03342   0.02515  -0.1050   0.3671   1.0000
  10.750   1.5506   0.03411   0.02589  -0.1034   0.3625   1.0000
  11.000   1.5455   0.03560   0.02758  -0.0997   0.3568   1.0000
  11.250   1.5563   0.03641   0.02845  -0.0979   0.3515   1.0000
  11.500   1.5705   0.03710   0.02919  -0.0965   0.3467   1.0000
  11.750   1.5580   0.03928   0.03158  -0.0929   0.3406   1.0000
  12.000   1.5663   0.04033   0.03269  -0.0912   0.3350   1.0000
  12.250   1.5717   0.04166   0.03410  -0.0895   0.3297   1.0000
  12.500   1.5566   0.04455   0.03719  -0.0868   0.3232   1.0000
  12.750   1.5687   0.04548   0.03815  -0.0857   0.3177   1.0000
  13.000   1.5539   0.04876   0.04160  -0.0838   0.3114   1.0000
  13.250   1.5451   0.05173   0.04471  -0.0825   0.3049   1.0000
  13.500   1.5578   0.05274   0.04573  -0.0817   0.2993   1.0000
  13.750   1.5216   0.05896   0.05219  -0.0807   0.2916   1.0000
  14.000   1.5381   0.05959   0.05282  -0.0801   0.2859   1.0000
  14.250   1.4971   0.06720   0.06065  -0.0803   0.2778   1.0000
  14.500   1.5057   0.06885   0.06234  -0.0799   0.2714   1.0000
  14.750   1.4703   0.07658   0.07024  -0.0809   0.2630   1.0000
  15.000   1.4779   0.07849   0.07219  -0.0808   0.2564   1.0000
  15.250   1.4443   0.08662   0.08047  -0.0826   0.2476   1.0000
  15.500   1.4572   0.08780   0.08168  -0.0823   0.2412   1.0000
  15.750   1.4252   0.09614   0.09016  -0.0846   0.2321   1.0000
  16.000   1.4432   0.09651   0.09055  -0.0842   0.2259   1.0000
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