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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.35 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e561-il-1000000.txt
Download as CSV file: xf-e561-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -0.5830   0.14519   0.14300  -0.0386   1.0000   0.0125
 -18.000  -0.6175   0.13373   0.13138  -0.0443   1.0000   0.0124
 -17.750  -0.6396   0.12530   0.12283  -0.0486   1.0000   0.0124
 -17.500  -0.6583   0.11796   0.11537  -0.0523   1.0000   0.0124
 -17.250  -0.6713   0.11188   0.10921  -0.0553   1.0000   0.0124
 -17.000  -0.6819   0.10637   0.10361  -0.0581   1.0000   0.0124
 -16.750  -0.6904   0.10146   0.09863  -0.0604   1.0000   0.0124
 -16.500  -0.6996   0.09639   0.09348  -0.0629   1.0000   0.0124
 -16.250  -0.7057   0.09204   0.08907  -0.0649   1.0000   0.0124
 -16.000  -0.7128   0.08767   0.08463  -0.0669   1.0000   0.0124
 -15.750  -0.7205   0.08314   0.08003  -0.0690   1.0000   0.0125
 -15.500  -0.7274   0.07923   0.07605  -0.0705   1.0000   0.0125
 -15.250  -0.7289   0.07604   0.07283  -0.0717   1.0000   0.0125
 -15.000  -0.7367   0.07230   0.06902  -0.0729   1.0000   0.0125
 -14.750  -0.7402   0.06904   0.06571  -0.0740   1.0000   0.0125
 -14.500  -0.7486   0.06573   0.06235  -0.0746   1.0000   0.0127
 -14.250  -0.7544   0.06269   0.05927  -0.0752   1.0000   0.0127
 -14.000  -0.7619   0.05953   0.05607  -0.0758   1.0000   0.0127
 -13.750  -0.7732   0.05642   0.05292  -0.0760   1.0000   0.0128
 -13.500  -0.7700   0.05273   0.04917  -0.0798   0.9988   0.0128
 -13.250  -0.7633   0.04857   0.04495  -0.0853   0.9965   0.0130
 -13.000  -0.7529   0.04458   0.04089  -0.0912   0.9942   0.0130
 -12.750  -0.7462   0.04052   0.03677  -0.0966   0.9907   0.0131
 -12.500  -0.7367   0.03634   0.03251  -0.1028   0.9863   0.0133
 -12.250  -0.7204   0.03223   0.02831  -0.1102   0.9833   0.0133
 -12.000  -0.7109   0.02790   0.02389  -0.1163   0.9750   0.0135
 -11.750  -0.6764   0.02335   0.01917  -0.1278   0.9720   0.0137
 -11.500  -0.6590   0.02143   0.01715  -0.1297   0.9633   0.0138
 -11.250  -0.6267   0.01995   0.01560  -0.1332   0.9603   0.0141
 -11.000  -0.6077   0.01882   0.01440  -0.1333   0.9504   0.0142
 -10.750  -0.5817   0.01775   0.01325  -0.1344   0.9430   0.0145
 -10.500  -0.5514   0.01677   0.01220  -0.1361   0.9356   0.0148
 -10.250  -0.5144   0.01588   0.01124  -0.1389   0.9296   0.0150
 -10.000  -0.4715   0.01515   0.01043  -0.1427   0.9219   0.0153
  -9.750  -0.4203   0.01379   0.00895  -0.1491   0.9144   0.0161
  -9.250  -0.3269   0.01254   0.00746  -0.1581   0.8803   0.0174
  -9.000  -0.2971   0.01219   0.00696  -0.1588   0.8569   0.0179
  -8.750  -0.2709   0.01193   0.00656  -0.1587   0.8350   0.0184
  -8.500  -0.2467   0.01154   0.00604  -0.1583   0.8148   0.0193
  -8.250  -0.2221   0.01124   0.00563  -0.1578   0.7967   0.0205
  -8.000  -0.1969   0.01101   0.00530  -0.1574   0.7804   0.0218
  -7.750  -0.1717   0.01068   0.00490  -0.1570   0.7647   0.0252
  -7.500  -0.1467   0.01018   0.00442  -0.1568   0.7500   0.0407
  -7.250  -0.1215   0.00963   0.00397  -0.1567   0.7359   0.0671
  -7.000  -0.0955   0.00929   0.00366  -0.1566   0.7227   0.0880
  -6.750  -0.0691   0.00907   0.00343  -0.1564   0.7100   0.1046
  -6.500  -0.0418   0.00884   0.00323  -0.1564   0.6981   0.1207
  -6.250  -0.0146   0.00870   0.00307  -0.1563   0.6864   0.1341
  -6.000   0.0123   0.00859   0.00293  -0.1561   0.6741   0.1473
  -5.750   0.0402   0.00849   0.00282  -0.1560   0.6629   0.1587
  -5.500   0.0678   0.00839   0.00271  -0.1559   0.6526   0.1711
  -5.250   0.0955   0.00832   0.00261  -0.1558   0.6420   0.1806
  -5.000   0.1236   0.00828   0.00254  -0.1558   0.6322   0.1902
  -4.500   0.1795   0.00819   0.00240  -0.1556   0.6122   0.2092
  -4.250   0.2071   0.00818   0.00235  -0.1555   0.6026   0.2190
  -4.000   0.2355   0.00814   0.00230  -0.1555   0.5939   0.2291
  -3.750   0.2633   0.00816   0.00227  -0.1553   0.5851   0.2371
  -3.500   0.2917   0.00812   0.00222  -0.1554   0.5766   0.2459
  -3.250   0.3194   0.00815   0.00220  -0.1552   0.5678   0.2528
  -3.000   0.3479   0.00813   0.00216  -0.1552   0.5597   0.2602
  -2.750   0.3756   0.00816   0.00215  -0.1551   0.5516   0.2675
  -2.500   0.4042   0.00816   0.00213  -0.1551   0.5446   0.2740
  -2.250   0.4321   0.00818   0.00213  -0.1550   0.5368   0.2822
  -2.000   0.4603   0.00821   0.00213  -0.1549   0.5296   0.2888
  -1.750   0.4884   0.00822   0.00213  -0.1549   0.5223   0.2969
  -1.500   0.5161   0.00828   0.00215  -0.1547   0.5155   0.3041
  -1.250   0.5446   0.00829   0.00216  -0.1548   0.5094   0.3114
  -1.000   0.5723   0.00834   0.00218  -0.1546   0.5025   0.3188
  -0.750   0.6002   0.00839   0.00221  -0.1545   0.4964   0.3250
  -0.500   0.6284   0.00841   0.00224  -0.1545   0.4904   0.3335
  -0.250   0.6558   0.00849   0.00228  -0.1543   0.4843   0.3403
   0.000   0.6838   0.00853   0.00232  -0.1543   0.4791   0.3473
   0.250   0.7119   0.00857   0.00236  -0.1542   0.4736   0.3551
   0.500   0.7391   0.00866   0.00242  -0.1540   0.4677   0.3618
   0.750   0.7668   0.00870   0.00248  -0.1539   0.4628   0.3695
   1.000   0.7948   0.00876   0.00253  -0.1538   0.4582   0.3767
   1.250   0.8221   0.00882   0.00259  -0.1537   0.4531   0.3846
   1.500   0.8488   0.00893   0.00268  -0.1534   0.4476   0.3923
   1.750   0.8769   0.00897   0.00274  -0.1533   0.4439   0.3996
   2.000   0.9045   0.00902   0.00282  -0.1532   0.4396   0.4084
   2.250   0.9312   0.00913   0.00290  -0.1529   0.4349   0.4161
   2.500   0.9579   0.00922   0.00301  -0.1527   0.4302   0.4252
   3.000   1.0128   0.00933   0.00318  -0.1524   0.4227   0.4451
   3.250   1.0393   0.00944   0.00328  -0.1521   0.4184   0.4551
   3.500   1.0651   0.00957   0.00342  -0.1517   0.4137   0.4672
   3.750   1.0927   0.00960   0.00352  -0.1516   0.4108   0.4808
   4.000   1.1196   0.00967   0.00363  -0.1514   0.4070   0.4950
   4.250   1.1457   0.00977   0.00375  -0.1511   0.4029   0.5114
   4.500   1.1710   0.00990   0.00391  -0.1506   0.3984   0.5308
   4.750   1.1976   0.00997   0.00405  -0.1504   0.3953   0.5537
   5.250   1.2502   0.01009   0.00434  -0.1498   0.3879   0.6114
   5.500   1.2751   0.01020   0.00453  -0.1493   0.3838   0.6497
   5.750   1.2999   0.01030   0.00473  -0.1488   0.3798   0.6953
   6.000   1.3259   0.01029   0.00490  -0.1484   0.3767   0.7565
   6.250   1.3481   0.01026   0.00509  -0.1472   0.3729   0.8450
   6.500   1.3636   0.01018   0.00520  -0.1446   0.3691   1.0000
   6.750   1.3855   0.01042   0.00541  -0.1435   0.3644   1.0000
   7.000   1.4108   0.01053   0.00555  -0.1430   0.3614   1.0000
   7.250   1.4349   0.01068   0.00571  -0.1423   0.3574   1.0000
   7.500   1.4573   0.01088   0.00590  -0.1414   0.3530   1.0000
   7.750   1.4779   0.01115   0.00614  -0.1401   0.3479   1.0000
   8.000   1.5025   0.01128   0.00630  -0.1395   0.3442   1.0000
   8.250   1.5253   0.01147   0.00650  -0.1386   0.3394   1.0000
   8.500   1.5457   0.01174   0.00675  -0.1374   0.3339   1.0000
   8.750   1.5679   0.01195   0.00698  -0.1364   0.3293   1.0000
   9.000   1.5898   0.01216   0.00720  -0.1354   0.3245   1.0000
   9.250   1.6090   0.01248   0.00749  -0.1340   0.3184   1.0000
   9.500   1.6300   0.01273   0.00776  -0.1329   0.3130   1.0000
   9.750   1.6501   0.01302   0.00805  -0.1317   0.3062   1.0000
  10.000   1.6674   0.01340   0.00841  -0.1300   0.2992   1.0000
  10.250   1.6867   0.01371   0.00874  -0.1287   0.2917   1.0000
  10.500   1.7027   0.01417   0.00916  -0.1269   0.2841   1.0000
  10.750   1.7197   0.01458   0.00957  -0.1253   0.2750   1.0000
  11.000   1.7345   0.01509   0.01006  -0.1234   0.2663   1.0000
  11.250   1.7482   0.01565   0.01060  -0.1213   0.2572   1.0000
  11.500   1.7625   0.01621   0.01116  -0.1194   0.2490   1.0000
  11.750   1.7725   0.01697   0.01187  -0.1170   0.2394   1.0000
  12.000   1.7850   0.01764   0.01255  -0.1150   0.2303   1.0000
  12.250   1.7930   0.01855   0.01342  -0.1125   0.2194   1.0000
  12.500   1.7991   0.01960   0.01444  -0.1099   0.2094   1.0000
  12.750   1.8063   0.02065   0.01547  -0.1076   0.1989   1.0000
  13.000   1.8111   0.02188   0.01669  -0.1051   0.1887   1.0000
  13.250   1.8134   0.02334   0.01813  -0.1026   0.1789   1.0000
  13.500   1.8140   0.02500   0.01976  -0.1001   0.1681   1.0000
  13.750   1.8138   0.02681   0.02156  -0.0978   0.1573   1.0000
  14.000   1.8121   0.02886   0.02360  -0.0956   0.1473   1.0000
  14.250   1.8079   0.03124   0.02596  -0.0935   0.1379   1.0000
  14.500   1.8034   0.03379   0.02850  -0.0917   0.1285   1.0000
  14.750   1.7994   0.03644   0.03116  -0.0902   0.1201   1.0000
  15.000   1.7914   0.03961   0.03433  -0.0888   0.1118   1.0000
  15.250   1.7853   0.04274   0.03748  -0.0878   0.1046   1.0000
  15.500   1.7789   0.04605   0.04082  -0.0870   0.0984   1.0000
  15.750   1.7696   0.04983   0.04462  -0.0863   0.0920   1.0000
  16.000   1.7629   0.05344   0.04828  -0.0860   0.0867   1.0000
  16.250   1.7532   0.05755   0.05242  -0.0858   0.0812   1.0000
  16.500   1.7458   0.06151   0.05643  -0.0858   0.0765   1.0000
  16.750   1.7346   0.06605   0.06100  -0.0860   0.0714   1.0000
  17.000   1.7262   0.07038   0.06539  -0.0864   0.0671   1.0000
  17.250   1.7156   0.07511   0.07016  -0.0870   0.0627   1.0000
  17.500   1.7060   0.07980   0.07490  -0.0878   0.0586   1.0000
  17.750   1.6960   0.08465   0.07980  -0.0887   0.0546   1.0000
  18.000   1.6858   0.08965   0.08484  -0.0898   0.0508   1.0000
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