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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 500,000
Max Cl/Cd: 105.02 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e561-il-500000.txt
Download as CSV file: xf-e561-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.5640   0.11659   0.11364  -0.0544   1.0000   0.0186
 -16.000  -0.5913   0.10719   0.10409  -0.0596   1.0000   0.0184
 -15.750  -0.6188   0.09846   0.09521  -0.0643   1.0000   0.0183
 -15.500  -0.6373   0.09170   0.08834  -0.0679   1.0000   0.0183
 -15.250  -0.6502   0.08635   0.08290  -0.0704   1.0000   0.0181
 -15.000  -0.6670   0.08041   0.07684  -0.0735   1.0000   0.0181
 -14.750  -0.6776   0.07577   0.07211  -0.0757   1.0000   0.0181
 -14.500  -0.6895   0.07106   0.06729  -0.0781   1.0000   0.0181
 -14.250  -0.6996   0.06699   0.06313  -0.0797   1.0000   0.0181
 -14.000  -0.7086   0.06337   0.05943  -0.0809   1.0000   0.0181
 -13.750  -0.7185   0.05987   0.05585  -0.0819   1.0000   0.0181
 -13.500  -0.7270   0.05677   0.05268  -0.0825   1.0000   0.0181
 -13.250  -0.7382   0.05353   0.04936  -0.0831   1.0000   0.0182
 -13.000  -0.7467   0.05100   0.04679  -0.0827   1.0000   0.0182
 -12.750  -0.7590   0.04835   0.04409  -0.0822   1.0000   0.0183
 -12.500  -0.7619   0.04541   0.04106  -0.0839   0.9989   0.0183
 -12.250  -0.7424   0.04224   0.03778  -0.0896   0.9953   0.0184
 -12.000  -0.7250   0.03930   0.03475  -0.0941   0.9913   0.0186
 -11.750  -0.7071   0.03662   0.03202  -0.0982   0.9860   0.0188
 -11.500  -0.6888   0.03381   0.02916  -0.1029   0.9803   0.0190
 -11.250  -0.6647   0.03064   0.02592  -0.1091   0.9737   0.0193
 -11.000  -0.6388   0.02749   0.02268  -0.1156   0.9660   0.0196
 -10.750  -0.6063   0.02513   0.02022  -0.1213   0.9612   0.0200
 -10.500  -0.5818   0.02347   0.01847  -0.1236   0.9531   0.0205
 -10.250  -0.5487   0.02202   0.01694  -0.1268   0.9485   0.0211
 -10.000  -0.5222   0.02080   0.01563  -0.1282   0.9405   0.0215
  -9.750  -0.4904   0.01954   0.01428  -0.1305   0.9350   0.0220
  -9.500  -0.4619   0.01801   0.01269  -0.1325   0.9267   0.0227
  -9.250  -0.4256   0.01686   0.01147  -0.1354   0.9206   0.0235
  -9.000  -0.3867   0.01592   0.01046  -0.1385   0.9136   0.0245
  -8.750  -0.3428   0.01509   0.00952  -0.1424   0.9057   0.0257
  -8.500  -0.2954   0.01406   0.00842  -0.1474   0.8967   0.0279
  -8.250  -0.2488   0.01329   0.00753  -0.1518   0.8847   0.0315
  -7.750  -0.1800   0.01152   0.00585  -0.1561   0.8499   0.0781
  -7.500  -0.1508   0.01109   0.00542  -0.1567   0.8319   0.1020
  -7.250  -0.1228   0.01082   0.00511  -0.1569   0.8146   0.1190
  -6.750  -0.0685   0.01047   0.00465  -0.1567   0.7829   0.1464
  -6.500  -0.0416   0.01037   0.00447  -0.1565   0.7682   0.1584
  -6.250  -0.0148   0.01025   0.00431  -0.1563   0.7538   0.1714
  -6.000   0.0121   0.01016   0.00417  -0.1560   0.7404   0.1834
  -5.500   0.0663   0.01007   0.00394  -0.1556   0.7150   0.2041
  -5.250   0.0934   0.01001   0.00383  -0.1553   0.7031   0.2135
  -5.000   0.1206   0.01003   0.00374  -0.1551   0.6914   0.2229
  -4.750   0.1478   0.00998   0.00368  -0.1549   0.6795   0.2338
  -4.500   0.1751   0.00996   0.00360  -0.1547   0.6687   0.2432
  -4.250   0.2024   0.00997   0.00354  -0.1544   0.6582   0.2514
  -4.000   0.2300   0.00993   0.00345  -0.1543   0.6479   0.2590
  -3.750   0.2572   0.00995   0.00340  -0.1540   0.6380   0.2667
  -3.500   0.2848   0.00994   0.00333  -0.1538   0.6278   0.2741
  -3.250   0.3122   0.00994   0.00330  -0.1536   0.6186   0.2818
  -3.000   0.3399   0.00998   0.00326  -0.1535   0.6093   0.2891
  -2.750   0.3673   0.00997   0.00323  -0.1533   0.6009   0.2971
  -2.500   0.3949   0.01000   0.00321  -0.1531   0.5919   0.3048
  -2.250   0.4224   0.01002   0.00319  -0.1529   0.5837   0.3123
  -2.000   0.4500   0.01005   0.00319  -0.1528   0.5751   0.3201
  -1.750   0.4774   0.01011   0.00318  -0.1526   0.5677   0.3277
  -1.500   0.5052   0.01011   0.00320  -0.1525   0.5600   0.3352
  -1.250   0.5324   0.01022   0.00321  -0.1522   0.5525   0.3426
  -1.000   0.5601   0.01021   0.00324  -0.1521   0.5453   0.3506
  -0.750   0.5875   0.01029   0.00326  -0.1519   0.5381   0.3582
  -0.500   0.6149   0.01034   0.00330  -0.1517   0.5318   0.3657
  -0.250   0.6426   0.01039   0.00334  -0.1516   0.5253   0.3740
   0.000   0.6696   0.01047   0.00338  -0.1514   0.5189   0.3816
   0.250   0.6971   0.01053   0.00344  -0.1512   0.5129   0.3894
   0.500   0.7246   0.01060   0.00349  -0.1511   0.5068   0.3976
   0.750   0.7515   0.01068   0.00356  -0.1508   0.5012   0.4059
   1.000   0.7790   0.01077   0.00364  -0.1507   0.4959   0.4142
   1.250   0.8063   0.01080   0.00372  -0.1505   0.4903   0.4229
   1.500   0.8331   0.01093   0.00379  -0.1502   0.4849   0.4322
   1.750   0.8602   0.01102   0.00390  -0.1501   0.4801   0.4410
   2.000   0.8875   0.01108   0.00399  -0.1499   0.4753   0.4511
   2.250   0.9143   0.01116   0.00409  -0.1497   0.4702   0.4613
   2.500   0.9408   0.01133   0.00422  -0.1494   0.4653   0.4721
   2.750   0.9679   0.01137   0.00434  -0.1492   0.4611   0.4841
   3.000   0.9947   0.01144   0.00446  -0.1490   0.4565   0.4971
   3.250   1.0210   0.01155   0.00459  -0.1487   0.4519   0.5112
   3.500   1.0475   0.01172   0.00476  -0.1485   0.4474   0.5272
   3.750   1.0741   0.01176   0.00491  -0.1482   0.4435   0.5464
   4.000   1.1004   0.01183   0.00507  -0.1479   0.4392   0.5686
   4.250   1.1263   0.01195   0.00523  -0.1476   0.4349   0.5953
   4.500   1.1524   0.01212   0.00545  -0.1473   0.4305   0.6285
   4.750   1.1781   0.01213   0.00565  -0.1469   0.4269   0.6701
   5.000   1.2030   0.01216   0.00585  -0.1463   0.4227   0.7229
   5.250   1.2256   0.01218   0.00606  -0.1452   0.4186   0.7959
   5.500   1.2399   0.01206   0.00617  -0.1421   0.4149   1.0000
   5.750   1.2656   0.01223   0.00636  -0.1417   0.4112   1.0000
   6.000   1.2907   0.01238   0.00654  -0.1413   0.4071   1.0000
   6.250   1.3154   0.01258   0.00672  -0.1407   0.4031   1.0000
   6.500   1.3397   0.01285   0.00694  -0.1402   0.3989   1.0000
   6.750   1.3640   0.01306   0.00717  -0.1396   0.3950   1.0000
   7.000   1.3871   0.01322   0.00737  -0.1387   0.3910   1.0000
   7.250   1.4093   0.01342   0.00758  -0.1377   0.3869   1.0000
   7.500   1.4314   0.01369   0.00781  -0.1367   0.3827   1.0000
   7.750   1.4536   0.01395   0.00809  -0.1358   0.3787   1.0000
   8.000   1.4747   0.01413   0.00833  -0.1346   0.3745   1.0000
   8.250   1.4954   0.01436   0.00858  -0.1334   0.3702   1.0000
   8.500   1.5156   0.01469   0.00887  -0.1321   0.3656   1.0000
   8.750   1.5360   0.01494   0.00917  -0.1309   0.3613   1.0000
   9.000   1.5556   0.01517   0.00946  -0.1295   0.3565   1.0000
   9.250   1.5740   0.01548   0.00976  -0.1280   0.3515   1.0000
   9.500   1.5923   0.01584   0.01013  -0.1265   0.3466   1.0000
   9.750   1.6112   0.01610   0.01047  -0.1250   0.3415   1.0000
  10.000   1.6283   0.01646   0.01084  -0.1234   0.3363   1.0000
  10.250   1.6442   0.01692   0.01129  -0.1216   0.3311   1.0000
  10.500   1.6621   0.01724   0.01171  -0.1202   0.3257   1.0000
  10.750   1.6770   0.01771   0.01218  -0.1183   0.3197   1.0000
  11.000   1.6911   0.01823   0.01273  -0.1164   0.3139   1.0000
  11.250   1.7059   0.01872   0.01326  -0.1146   0.3067   1.0000
  11.500   1.7162   0.01944   0.01397  -0.1123   0.2997   1.0000
  11.750   1.7299   0.02002   0.01462  -0.1106   0.2916   1.0000
  12.000   1.7382   0.02090   0.01549  -0.1082   0.2838   1.0000
  12.250   1.7501   0.02167   0.01630  -0.1064   0.2755   1.0000
  12.500   1.7570   0.02273   0.01736  -0.1042   0.2675   1.0000
  12.750   1.7661   0.02374   0.01841  -0.1023   0.2591   1.0000
  13.000   1.7719   0.02500   0.01968  -0.1002   0.2513   1.0000
  13.250   1.7773   0.02636   0.02107  -0.0982   0.2426   1.0000
  13.500   1.7817   0.02785   0.02259  -0.0963   0.2343   1.0000
  13.750   1.7819   0.02974   0.02447  -0.0943   0.2254   1.0000
  14.000   1.7852   0.03150   0.02627  -0.0927   0.2165   1.0000
  14.250   1.7824   0.03384   0.02863  -0.0910   0.2073   1.0000
  14.500   1.7792   0.03636   0.03116  -0.0895   0.1973   1.0000
  14.750   1.7763   0.03898   0.03380  -0.0882   0.1879   1.0000
  15.000   1.7687   0.04217   0.03699  -0.0870   0.1793   1.0000
  15.250   1.7617   0.04547   0.04032  -0.0860   0.1695   1.0000
  15.500   1.7539   0.04899   0.04387  -0.0853   0.1606   1.0000
  15.750   1.7413   0.05319   0.04808  -0.0848   0.1521   1.0000
  16.000   1.7324   0.05714   0.05206  -0.0846   0.1433   1.0000
  16.250   1.7209   0.06154   0.05650  -0.0846   0.1359   1.0000
  16.500   1.7091   0.06611   0.06111  -0.0848   0.1284   1.0000
  16.750   1.6992   0.07058   0.06562  -0.0852   0.1219   1.0000
  17.000   1.6866   0.07554   0.07061  -0.0858   0.1153   1.0000
  17.250   1.6772   0.08016   0.07530  -0.0865   0.1094   1.0000
  17.500   1.6648   0.08532   0.08049  -0.0875   0.1034   1.0000
  17.750   1.6555   0.09013   0.08536  -0.0885   0.0981   1.0000
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