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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 200,000
Max Cl/Cd: 74.1 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e561-il-200000-n5.txt
Download as CSV file: xf-e561-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.5319   0.10163   0.09711  -0.0611   1.0000   0.0196
 -14.500  -0.5514   0.09455   0.08991  -0.0645   1.0000   0.0196
 -14.250  -0.5649   0.08895   0.08420  -0.0670   1.0000   0.0196
 -14.000  -0.5752   0.08412   0.07929  -0.0690   1.0000   0.0197
 -13.750  -0.5841   0.07974   0.07484  -0.0707   1.0000   0.0198
 -13.500  -0.5917   0.07582   0.07085  -0.0720   1.0000   0.0198
 -13.250  -0.5986   0.07220   0.06717  -0.0731   1.0000   0.0199
 -13.000  -0.6058   0.06881   0.06373  -0.0739   1.0000   0.0200
 -12.750  -0.6139   0.06561   0.06050  -0.0744   1.0000   0.0201
 -12.500  -0.6230   0.06255   0.05739  -0.0746   1.0000   0.0203
 -12.250  -0.6326   0.05971   0.05452  -0.0745   1.0000   0.0203
 -12.000  -0.6451   0.05686   0.05165  -0.0741   1.0000   0.0205
 -11.750  -0.6315   0.05320   0.04789  -0.0794   0.9959   0.0207
 -11.500  -0.6184   0.04969   0.04428  -0.0844   0.9907   0.0210
 -11.250  -0.6053   0.04619   0.04067  -0.0895   0.9844   0.0214
 -11.000  -0.5959   0.04289   0.03729  -0.0936   0.9753   0.0215
 -10.750  -0.5911   0.03954   0.03385  -0.0971   0.9630   0.0218
 -10.500  -0.5849   0.03576   0.02999  -0.1017   0.9490   0.0221
 -10.250  -0.5693   0.03162   0.02572  -0.1085   0.9358   0.0225
 -10.000  -0.5478   0.02869   0.02264  -0.1136   0.9244   0.0231
  -9.750  -0.5176   0.02658   0.02038  -0.1180   0.9176   0.0242
  -9.500  -0.4919   0.02502   0.01867  -0.1202   0.9065   0.0253
  -9.250  -0.4592   0.02337   0.01691  -0.1237   0.8988   0.0267
  -9.000  -0.4256   0.02203   0.01544  -0.1267   0.8895   0.0283
  -8.750  -0.3876   0.02077   0.01404  -0.1302   0.8809   0.0306
  -8.500  -0.3468   0.01958   0.01272  -0.1341   0.8714   0.0345
  -8.250  -0.3075   0.01845   0.01152  -0.1376   0.8604   0.0415
  -8.000  -0.2665   0.01736   0.01039  -0.1414   0.8491   0.0559
  -7.750  -0.2291   0.01648   0.00951  -0.1442   0.8355   0.0759
  -7.500  -0.1948   0.01585   0.00885  -0.1461   0.8213   0.0948
  -7.250  -0.1618   0.01538   0.00831  -0.1476   0.8070   0.1116
  -7.000  -0.1302   0.01503   0.00788  -0.1486   0.7928   0.1266
  -6.750  -0.0998   0.01474   0.00751  -0.1493   0.7790   0.1445
  -6.500  -0.0709   0.01450   0.00723  -0.1497   0.7651   0.1623
  -6.250  -0.0427   0.01433   0.00700  -0.1499   0.7517   0.1776
  -6.000  -0.0143   0.01422   0.00676  -0.1500   0.7391   0.1905
  -5.750   0.0139   0.01411   0.00656  -0.1501   0.7268   0.2012
  -5.500   0.0413   0.01400   0.00637  -0.1500   0.7143   0.2104
  -5.250   0.0690   0.01393   0.00617  -0.1499   0.7030   0.2200
  -4.750   0.1239   0.01380   0.00583  -0.1496   0.6808   0.2368
  -4.500   0.1513   0.01373   0.00571  -0.1495   0.6703   0.2445
  -4.250   0.1787   0.01370   0.00555  -0.1493   0.6598   0.2528
  -4.000   0.2061   0.01365   0.00545  -0.1491   0.6502   0.2601
  -3.750   0.2335   0.01364   0.00533  -0.1490   0.6407   0.2682
  -3.500   0.2608   0.01361   0.00524  -0.1488   0.6312   0.2758
  -3.250   0.2881   0.01362   0.00516  -0.1486   0.6221   0.2837
  -3.000   0.3155   0.01360   0.00507  -0.1484   0.6129   0.2913
  -2.750   0.3428   0.01362   0.00503  -0.1482   0.6048   0.2989
  -2.500   0.3703   0.01363   0.00496  -0.1480   0.5965   0.3069
  -2.250   0.3974   0.01364   0.00494  -0.1478   0.5883   0.3139
  -2.000   0.4248   0.01367   0.00490  -0.1476   0.5804   0.3222
  -1.750   0.4519   0.01370   0.00489  -0.1474   0.5725   0.3292
  -1.500   0.4792   0.01375   0.00489  -0.1472   0.5656   0.3371
  -1.250   0.5065   0.01379   0.00488  -0.1470   0.5582   0.3448
  -1.000   0.5336   0.01386   0.00490  -0.1468   0.5516   0.3525
  -0.750   0.5609   0.01391   0.00491  -0.1466   0.5444   0.3605
  -0.500   0.5878   0.01396   0.00495  -0.1464   0.5377   0.3680
  -0.250   0.6150   0.01405   0.00498  -0.1462   0.5318   0.3765
   0.000   0.6421   0.01410   0.00505  -0.1460   0.5254   0.3840
   0.250   0.6690   0.01419   0.00510  -0.1457   0.5194   0.3926
   0.500   0.6959   0.01428   0.00517  -0.1455   0.5136   0.4007
   0.750   0.7228   0.01435   0.00526  -0.1453   0.5076   0.4092
   1.000   0.7495   0.01446   0.00534  -0.1450   0.5023   0.4180
   1.250   0.7763   0.01457   0.00545  -0.1448   0.4974   0.4271
   1.500   0.8031   0.01465   0.00556  -0.1446   0.4916   0.4361
   1.750   0.8294   0.01476   0.00568  -0.1443   0.4863   0.4458
   2.000   0.8560   0.01491   0.00579  -0.1440   0.4818   0.4559
   2.250   0.8825   0.01500   0.00595  -0.1437   0.4768   0.4667
   2.500   0.9088   0.01511   0.00611  -0.1434   0.4717   0.4776
   2.750   0.9349   0.01526   0.00625  -0.1431   0.4671   0.4900
   3.000   0.9610   0.01540   0.00643  -0.1428   0.4627   0.5032
   3.250   0.9870   0.01551   0.00663  -0.1424   0.4580   0.5175
   3.500   1.0126   0.01565   0.00682  -0.1420   0.4534   0.5334
   3.750   1.0380   0.01581   0.00701  -0.1416   0.4492   0.5512
   4.000   1.0635   0.01595   0.00724  -0.1411   0.4449   0.5718
   4.250   1.0886   0.01608   0.00749  -0.1407   0.4404   0.5956
   4.500   1.1133   0.01622   0.00772  -0.1401   0.4361   0.6230
   4.750   1.1376   0.01638   0.00795  -0.1394   0.4322   0.6565
   5.000   1.1612   0.01651   0.00823  -0.1386   0.4281   0.6983
   5.250   1.1832   0.01659   0.00851  -0.1374   0.4238   0.7515
   5.500   1.2006   0.01661   0.00872  -0.1351   0.4197   0.8330
   5.750   1.2201   0.01663   0.00882  -0.1333   0.4160   1.0000
   6.000   1.2450   0.01691   0.00910  -0.1329   0.4121   1.0000
   6.250   1.2689   0.01718   0.00941  -0.1323   0.4077   1.0000
   6.500   1.2925   0.01746   0.00970  -0.1317   0.4033   1.0000
   6.750   1.3160   0.01776   0.00998  -0.1310   0.3994   1.0000
   7.000   1.3394   0.01808   0.01029  -0.1304   0.3956   1.0000
   7.250   1.3613   0.01838   0.01066  -0.1294   0.3911   1.0000
   7.500   1.3826   0.01868   0.01100  -0.1284   0.3867   1.0000
   7.750   1.4037   0.01901   0.01131  -0.1273   0.3828   1.0000
   8.000   1.4242   0.01935   0.01168  -0.1262   0.3788   1.0000
   8.250   1.4430   0.01969   0.01211  -0.1248   0.3742   1.0000
   8.500   1.4619   0.02005   0.01251  -0.1234   0.3697   1.0000
   8.750   1.4809   0.02043   0.01288  -0.1220   0.3656   1.0000
   9.000   1.4988   0.02084   0.01336  -0.1205   0.3612   1.0000
   9.250   1.5157   0.02125   0.01386  -0.1189   0.3563   1.0000
   9.500   1.5321   0.02169   0.01433  -0.1172   0.3516   1.0000
   9.750   1.5486   0.02217   0.01480  -0.1156   0.3472   1.0000
  10.000   1.5630   0.02267   0.01544  -0.1137   0.3418   1.0000
  10.250   1.5769   0.02320   0.01603  -0.1118   0.3364   1.0000
  10.500   1.5904   0.02379   0.01661  -0.1099   0.3315   1.0000
  10.750   1.6026   0.02443   0.01738  -0.1079   0.3256   1.0000
  11.000   1.6136   0.02513   0.01814  -0.1058   0.3198   1.0000
  11.250   1.6243   0.02590   0.01894  -0.1038   0.3144   1.0000
  11.500   1.6341   0.02675   0.01990  -0.1018   0.3081   1.0000
  11.750   1.6423   0.02770   0.02088  -0.0997   0.3022   1.0000
  12.000   1.6507   0.02872   0.02200  -0.0978   0.2962   1.0000
  12.250   1.6574   0.02988   0.02324  -0.0959   0.2896   1.0000
  12.500   1.6628   0.03117   0.02456  -0.0940   0.2835   1.0000
  12.750   1.6679   0.03258   0.02608  -0.0922   0.2764   1.0000
  13.000   1.6701   0.03423   0.02773  -0.0903   0.2697   1.0000
  13.250   1.6736   0.03592   0.02955  -0.0888   0.2622   1.0000
  13.500   1.6733   0.03796   0.03160  -0.0872   0.2550   1.0000
  13.750   1.6745   0.04003   0.03378  -0.0859   0.2474   1.0000
  14.000   1.6714   0.04253   0.03631  -0.0846   0.2398   1.0000
  14.250   1.6700   0.04505   0.03892  -0.0836   0.2315   1.0000
  14.500   1.6639   0.04810   0.04200  -0.0827   0.2235   1.0000
  14.750   1.6599   0.05114   0.04512  -0.0821   0.2149   1.0000
  15.000   1.6524   0.05465   0.04867  -0.0816   0.2066   1.0000
  15.250   1.6449   0.05832   0.05240  -0.0813   0.1980   1.0000
  15.500   1.6369   0.06220   0.05633  -0.0813   0.1897   1.0000
  15.750   1.6257   0.06659   0.06075  -0.0814   0.1813   1.0000
  16.000   1.6174   0.07080   0.06504  -0.0818   0.1726   1.0000
  16.250   1.6059   0.07551   0.06977  -0.0824   0.1648   1.0000
  16.500   1.5958   0.08019   0.07451  -0.0831   0.1563   1.0000
  16.750   1.5853   0.08502   0.07939  -0.0840   0.1486   1.0000
  17.000   1.5734   0.09015   0.08455  -0.0852   0.1408   1.0000
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