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EPPLER 557 AIRFOIL (e557-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 557 AIRFOIL (e557-il)
Reynolds number: 200,000
Max Cl/Cd: 75.01 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e557-il-200000.txt
Download as CSV file: xf-e557-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 557 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.4515   0.10259   0.09893  -0.0565   1.0000   0.0314
 -12.250  -0.6232   0.06840   0.06397  -0.0773   1.0000   0.0224
 -12.000  -0.6413   0.06420   0.05969  -0.0782   1.0000   0.0223
 -11.750  -0.6599   0.06054   0.05593  -0.0786   1.0000   0.0223
 -11.500  -0.6727   0.05743   0.05277  -0.0779   1.0000   0.0220
 -11.250  -0.7052   0.05449   0.04966  -0.0769   1.0000   0.0223
 -11.000  -0.7211   0.05233   0.04746  -0.0747   1.0000   0.0222
 -10.750  -0.7435   0.05050   0.04559  -0.0714   1.0000   0.0220
 -10.500  -0.7730   0.04913   0.04414  -0.0678   1.0000   0.0221
 -10.250  -0.7843   0.04693   0.04185  -0.0661   1.0000   0.0219
 -10.000  -0.7896   0.04391   0.03842  -0.0673   0.9981   0.0223
  -9.750  -0.7654   0.03987   0.03394  -0.0721   0.9933   0.0228
  -9.500  -0.7364   0.03808   0.03221  -0.0745   0.9886   0.0239
  -9.250  -0.7049   0.03573   0.02963  -0.0779   0.9845   0.0250
  -9.000  -0.6776   0.03334   0.02694  -0.0797   0.9791   0.0255
  -8.750  -0.6452   0.03121   0.02447  -0.0820   0.9748   0.0266
  -8.500  -0.6155   0.02932   0.02255  -0.0833   0.9708   0.0281
  -8.250  -0.5854   0.02799   0.02120  -0.0847   0.9651   0.0299
  -8.000  -0.5497   0.02652   0.01966  -0.0874   0.9617   0.0333
  -7.750  -0.5208   0.02546   0.01858  -0.0888   0.9550   0.0373
  -7.500  -0.4866   0.02395   0.01711  -0.0914   0.9505   0.0425
  -7.250  -0.4462   0.02259   0.01576  -0.0953   0.9477   0.0516
  -7.000  -0.4187   0.02138   0.01456  -0.0967   0.9397   0.0612
  -6.750  -0.3786   0.01984   0.01310  -0.1009   0.9360   0.0793
  -6.500  -0.3344   0.01818   0.01160  -0.1060   0.9337   0.1165
  -6.250  -0.2978   0.01575   0.00998  -0.1111   0.9280   0.2554
  -6.000  -0.2587   0.01548   0.01003  -0.1137   0.9230   0.3690
  -5.750  -0.2159   0.01567   0.01012  -0.1162   0.9200   0.4011
  -5.500  -0.1713   0.01587   0.01017  -0.1190   0.9180   0.4228
  -5.250  -0.1453   0.01616   0.01046  -0.1182   0.9087   0.4343
  -5.000  -0.1038   0.01626   0.01050  -0.1203   0.9057   0.4465
  -4.750  -0.0586   0.01624   0.01035  -0.1234   0.9036   0.4586
  -4.500  -0.0284   0.01642   0.01056  -0.1232   0.8960   0.4657
  -4.250   0.0130   0.01636   0.01039  -0.1256   0.8915   0.4759
  -4.000   0.0551   0.01664   0.01070  -0.1275   0.8882   0.4872
  -3.750   0.0874   0.01662   0.01064  -0.1281   0.8805   0.4944
  -3.500   0.1256   0.01641   0.01038  -0.1299   0.8744   0.4988
  -3.250   0.1706   0.01602   0.00984  -0.1334   0.8700   0.5042
  -3.000   0.1996   0.01574   0.00942  -0.1339   0.8595   0.5085
  -2.750   0.2393   0.01549   0.00913  -0.1361   0.8536   0.5117
  -2.500   0.2668   0.01536   0.00895  -0.1359   0.8429   0.5149
  -2.250   0.3013   0.01516   0.00865  -0.1373   0.8346   0.5189
  -2.000   0.3340   0.01496   0.00829  -0.1385   0.8250   0.5239
  -1.750   0.3633   0.01481   0.00810  -0.1387   0.8152   0.5267
  -1.500   0.3958   0.01468   0.00791  -0.1395   0.8065   0.5297
  -1.250   0.4227   0.01462   0.00782  -0.1393   0.7957   0.5332
  -1.000   0.4552   0.01453   0.00761  -0.1402   0.7870   0.5378
  -0.750   0.4836   0.01443   0.00742  -0.1405   0.7764   0.5420
  -0.500   0.5113   0.01438   0.00736  -0.1403   0.7665   0.5448
  -0.250   0.5413   0.01433   0.00726  -0.1407   0.7574   0.5482
   0.000   0.5678   0.01432   0.00723  -0.1404   0.7467   0.5523
   0.250   0.5989   0.01431   0.00709  -0.1411   0.7378   0.5573
   0.500   0.6251   0.01427   0.00707  -0.1407   0.7273   0.5608
   0.750   0.6523   0.01429   0.00709  -0.1405   0.7175   0.5643
   1.000   0.6813   0.01430   0.00704  -0.1407   0.7083   0.5686
   1.250   0.7082   0.01434   0.00704  -0.1406   0.6977   0.5734
   1.500   0.7370   0.01436   0.00702  -0.1408   0.6888   0.5774
   1.750   0.7624   0.01440   0.00711  -0.1402   0.6783   0.5816
   2.000   0.7896   0.01447   0.00716  -0.1401   0.6685   0.5866
   2.250   0.8186   0.01453   0.00713  -0.1403   0.6591   0.5919
   2.500   0.8433   0.01457   0.00726  -0.1397   0.6486   0.5957
   2.750   0.8712   0.01466   0.00733  -0.1396   0.6394   0.6006
   3.000   0.8972   0.01475   0.00741  -0.1393   0.6288   0.6066
   3.250   0.9230   0.01484   0.00754  -0.1389   0.6187   0.6116
   3.500   0.9504   0.01494   0.00762  -0.1387   0.6091   0.6172
   3.750   0.9751   0.01505   0.00776  -0.1381   0.5979   0.6235
   4.000   1.0008   0.01515   0.00789  -0.1377   0.5877   0.6287
   4.250   1.0267   0.01526   0.00801  -0.1372   0.5773   0.6350
   4.500   1.0510   0.01539   0.00819  -0.1366   0.5660   0.6423
   4.750   1.0758   0.01552   0.00837  -0.1359   0.5555   0.6487
   5.000   1.1013   0.01568   0.00851  -0.1355   0.5448   0.6570
   5.250   1.1240   0.01580   0.00874  -0.1345   0.5333   0.6636
   5.500   1.1486   0.01598   0.00895  -0.1339   0.5225   0.6724
   5.750   1.1725   0.01615   0.00914  -0.1331   0.5115   0.6806
   6.000   1.1945   0.01632   0.00939  -0.1320   0.4994   0.6910
   6.250   1.2164   0.01650   0.00967  -0.1308   0.4878   0.7003
   6.500   1.2389   0.01670   0.00989  -0.1298   0.4761   0.7112
   6.750   1.2603   0.01691   0.01015  -0.1286   0.4635   0.7237
   7.000   1.2796   0.01710   0.01047  -0.1270   0.4506   0.7363
   7.250   1.2988   0.01732   0.01079  -0.1254   0.4377   0.7509
   7.500   1.3172   0.01756   0.01110  -0.1236   0.4245   0.7676
   7.750   1.3346   0.01782   0.01142  -0.1217   0.4110   0.7872
   8.000   1.3496   0.01808   0.01176  -0.1193   0.3971   0.8096
   8.250   1.3614   0.01830   0.01211  -0.1162   0.3828   0.8409
   8.500   1.3630   0.01830   0.01230  -0.1110   0.3698   0.9130
   8.750   1.3765   0.01868   0.01266  -0.1088   0.3538   1.0000
   9.000   1.3899   0.01925   0.01318  -0.1066   0.3369   1.0000
   9.250   1.4012   0.01990   0.01379  -0.1041   0.3197   1.0000
   9.500   1.4108   0.02063   0.01447  -0.1015   0.3020   1.0000
   9.750   1.4197   0.02142   0.01524  -0.0988   0.2835   1.0000
  10.000   1.4270   0.02233   0.01612  -0.0960   0.2649   1.0000
  10.250   1.4327   0.02339   0.01713  -0.0932   0.2468   1.0000
  10.500   1.4373   0.02459   0.01828  -0.0904   0.2296   1.0000
  10.750   1.4411   0.02591   0.01955  -0.0877   0.2135   1.0000
  11.000   1.4445   0.02735   0.02095  -0.0852   0.1983   1.0000
  11.250   1.4476   0.02890   0.02248  -0.0829   0.1842   1.0000
  11.500   1.4503   0.03056   0.02413  -0.0807   0.1710   1.0000
  11.750   1.4523   0.03237   0.02593  -0.0786   0.1589   1.0000
  12.000   1.4529   0.03438   0.02791  -0.0767   0.1481   1.0000
  12.250   1.4532   0.03652   0.03005  -0.0750   0.1378   1.0000
  12.500   1.4557   0.03858   0.03216  -0.0736   0.1277   1.0000
  12.750   1.4554   0.04098   0.03457  -0.0723   0.1191   1.0000
  13.000   1.4545   0.04353   0.03712  -0.0711   0.1111   1.0000
  13.250   1.4557   0.04600   0.03967  -0.0702   0.1033   1.0000
  13.500   1.4521   0.04902   0.04265  -0.0693   0.0971   1.0000
  13.750   1.4540   0.05164   0.04539  -0.0688   0.0903   1.0000
  14.000   1.4499   0.05494   0.04866  -0.0683   0.0849   1.0000
  14.250   1.4509   0.05784   0.05169  -0.0680   0.0794   1.0000
  14.500   1.4483   0.06120   0.05508  -0.0680   0.0747   1.0000
  14.750   1.4469   0.06454   0.05849  -0.0679   0.0702   1.0000
  15.000   1.4462   0.06790   0.06195  -0.0681   0.0659   1.0000
  15.250   1.4424   0.07159   0.06556  -0.0682   0.0622   1.0000
  15.500   1.4426   0.07507   0.06925  -0.0688   0.0587   1.0000
  15.750   1.4411   0.07879   0.07303  -0.0695   0.0555   1.0000
  16.000   1.4394   0.08240   0.07660  -0.0698   0.0524   1.0000
  16.250   1.4382   0.08629   0.08069  -0.0708   0.0497   1.0000
  16.500   1.4369   0.09017   0.08464  -0.0718   0.0472   1.0000
  16.750   1.4381   0.09340   0.08779  -0.0722   0.0445   1.0000
  17.000   1.4349   0.09781   0.09243  -0.0737   0.0426   1.0000
  17.250   1.4330   0.10194   0.09669  -0.0751   0.0406   1.0000
  17.500   1.4325   0.10578   0.10056  -0.0765   0.0388   1.0000
  17.750   1.4342   0.10908   0.10387  -0.0772   0.0368   1.0000
  18.000   1.4300   0.11382   0.10882  -0.0792   0.0353   1.0000
  18.250   1.4276   0.11817   0.11329  -0.0812   0.0338   1.0000
  18.500   1.4282   0.12187   0.11701  -0.0828   0.0323   1.0000
  18.750   1.4306   0.12504   0.12019  -0.0839   0.0308   1.0000
  19.000   1.4238   0.13041   0.12580  -0.0867   0.0298   1.0000
  19.250   1.4188   0.13542   0.13097  -0.0895   0.0286   1.0000
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