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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 500,000
Max Cl/Cd: 104.2 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e561-il-500000-n5.txt
Download as CSV file: xf-e561-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -0.5819   0.13682   0.13368  -0.0438   1.0000   0.0117
 -17.500  -0.5988   0.12945   0.12620  -0.0473   1.0000   0.0117
 -17.250  -0.6086   0.12376   0.12042  -0.0499   1.0000   0.0117
 -17.000  -0.6181   0.11828   0.11486  -0.0524   1.0000   0.0118
 -16.750  -0.6247   0.11349   0.11000  -0.0545   1.0000   0.0118
 -16.500  -0.6312   0.10878   0.10522  -0.0566   1.0000   0.0119
 -16.250  -0.6373   0.10426   0.10063  -0.0586   1.0000   0.0119
 -16.000  -0.6420   0.10009   0.09640  -0.0603   1.0000   0.0120
 -15.750  -0.6485   0.09564   0.09188  -0.0622   1.0000   0.0121
 -15.500  -0.6518   0.09190   0.08809  -0.0636   1.0000   0.0121
 -15.250  -0.6551   0.08831   0.08446  -0.0650   1.0000   0.0121
 -15.000  -0.6605   0.08436   0.08044  -0.0665   1.0000   0.0122
 -14.750  -0.6639   0.08093   0.07698  -0.0676   1.0000   0.0122
 -14.500  -0.6689   0.07727   0.07326  -0.0689   1.0000   0.0123
 -14.250  -0.6741   0.07377   0.06971  -0.0700   1.0000   0.0123
 -14.000  -0.6791   0.07044   0.06635  -0.0709   1.0000   0.0123
 -13.750  -0.6859   0.06694   0.06279  -0.0719   1.0000   0.0124
 -13.500  -0.6782   0.06300   0.05878  -0.0763   0.9985   0.0124
 -13.250  -0.6735   0.05876   0.05450  -0.0810   0.9963   0.0126
 -13.000  -0.6676   0.05464   0.05031  -0.0860   0.9940   0.0127
 -12.750  -0.6661   0.05029   0.04590  -0.0907   0.9907   0.0128
 -12.500  -0.6630   0.04598   0.04153  -0.0958   0.9866   0.0130
 -12.250  -0.6542   0.04174   0.03720  -0.1018   0.9830   0.0131
 -12.000  -0.6582   0.03776   0.03315  -0.1050   0.9741   0.0132
 -11.750  -0.6656   0.03377   0.02908  -0.1078   0.9610   0.0133
 -11.500  -0.6655   0.02953   0.02472  -0.1120   0.9447   0.0133
 -11.250  -0.6443   0.02525   0.02028  -0.1202   0.9335   0.0136
 -11.000  -0.6178   0.02306   0.01794  -0.1245   0.9232   0.0138
 -10.750  -0.5821   0.02136   0.01612  -0.1291   0.9161   0.0141
 -10.500  -0.5427   0.01996   0.01460  -0.1336   0.9068   0.0145
 -10.250  -0.4933   0.01870   0.01320  -0.1398   0.8979   0.0149
 -10.000  -0.4400   0.01764   0.01198  -0.1464   0.8858   0.0153
  -9.750  -0.3976   0.01658   0.01077  -0.1509   0.8668   0.0159
  -9.500  -0.3649   0.01591   0.00995  -0.1529   0.8454   0.0165
  -9.250  -0.3373   0.01540   0.00928  -0.1535   0.8248   0.0171
  -9.000  -0.3118   0.01498   0.00871  -0.1536   0.8058   0.0177
  -8.750  -0.2869   0.01461   0.00820  -0.1534   0.7884   0.0184
  -8.500  -0.2624   0.01419   0.00766  -0.1532   0.7722   0.0195
  -8.250  -0.2377   0.01383   0.00719  -0.1529   0.7569   0.0212
  -8.000  -0.2129   0.01345   0.00672  -0.1527   0.7428   0.0241
  -7.750  -0.1879   0.01304   0.00626  -0.1525   0.7292   0.0303
  -7.500  -0.1626   0.01259   0.00580  -0.1524   0.7161   0.0423
  -7.250  -0.1370   0.01220   0.00539  -0.1523   0.7036   0.0557
  -7.000  -0.1112   0.01187   0.00504  -0.1521   0.6917   0.0697
  -6.750  -0.0846   0.01156   0.00473  -0.1521   0.6804   0.0839
  -6.500  -0.0579   0.01130   0.00446  -0.1520   0.6697   0.0980
  -6.250  -0.0313   0.01108   0.00423  -0.1519   0.6582   0.1140
  -6.000  -0.0041   0.01087   0.00402  -0.1519   0.6475   0.1306
  -5.750   0.0229   0.01071   0.00385  -0.1518   0.6376   0.1458
  -5.500   0.0506   0.01059   0.00370  -0.1517   0.6281   0.1580
  -5.250   0.0779   0.01048   0.00356  -0.1516   0.6189   0.1694
  -5.000   0.1056   0.01039   0.00345  -0.1516   0.6092   0.1804
  -4.750   0.1330   0.01032   0.00335  -0.1515   0.6000   0.1930
  -4.500   0.1608   0.01027   0.00326  -0.1514   0.5908   0.2050
  -4.250   0.1885   0.01022   0.00318  -0.1513   0.5831   0.2138
  -4.000   0.2164   0.01020   0.00311  -0.1512   0.5748   0.2212
  -3.750   0.2440   0.01017   0.00304  -0.1511   0.5670   0.2283
  -3.500   0.2720   0.01015   0.00298  -0.1510   0.5586   0.2358
  -3.250   0.2994   0.01016   0.00293  -0.1508   0.5509   0.2423
  -3.000   0.3276   0.01014   0.00289  -0.1508   0.5438   0.2501
  -2.750   0.3553   0.01016   0.00286  -0.1507   0.5367   0.2569
  -2.500   0.3832   0.01015   0.00284  -0.1506   0.5301   0.2646
  -2.250   0.4110   0.01018   0.00282  -0.1505   0.5228   0.2715
  -2.000   0.4384   0.01020   0.00281  -0.1503   0.5160   0.2787
  -1.750   0.4665   0.01022   0.00281  -0.1503   0.5098   0.2863
  -1.500   0.4942   0.01025   0.00281  -0.1501   0.5037   0.2925
  -1.250   0.5216   0.01029   0.00283  -0.1500   0.4979   0.3002
  -1.000   0.5496   0.01033   0.00284  -0.1499   0.4919   0.3072
  -0.750   0.5770   0.01037   0.00288  -0.1497   0.4857   0.3141
  -0.500   0.6044   0.01043   0.00291  -0.1495   0.4805   0.3214
  -0.250   0.6323   0.01047   0.00295  -0.1495   0.4754   0.3286
   0.000   0.6596   0.01053   0.00300  -0.1493   0.4699   0.3359
   0.500   0.7143   0.01065   0.00311  -0.1489   0.4599   0.3501
   0.750   0.7416   0.01072   0.00317  -0.1488   0.4549   0.3576
   1.000   0.7684   0.01081   0.00324  -0.1485   0.4503   0.3642
   1.250   0.7955   0.01089   0.00333  -0.1483   0.4459   0.3721
   1.500   0.8228   0.01096   0.00340  -0.1481   0.4412   0.3794
   1.750   0.8496   0.01104   0.00349  -0.1479   0.4366   0.3869
   2.000   0.8760   0.01115   0.00359  -0.1476   0.4325   0.3949
   2.250   0.9029   0.01123   0.00370  -0.1473   0.4286   0.4028
   2.500   0.9299   0.01131   0.00380  -0.1471   0.4243   0.4112
   2.750   0.9563   0.01141   0.00392  -0.1468   0.4199   0.4193
   3.000   0.9822   0.01153   0.00404  -0.1464   0.4160   0.4290
   3.250   1.0084   0.01164   0.00417  -0.1461   0.4124   0.4380
   3.500   1.0350   0.01173   0.00431  -0.1458   0.4085   0.4481
   3.750   1.0611   0.01183   0.00445  -0.1455   0.4044   0.4593
   4.250   1.1115   0.01211   0.00477  -0.1445   0.3968   0.4837
   4.500   1.1378   0.01219   0.00492  -0.1442   0.3932   0.4982
   4.750   1.1633   0.01230   0.00509  -0.1438   0.3893   0.5145
   5.000   1.1882   0.01244   0.00528  -0.1432   0.3853   0.5322
   5.250   1.2120   0.01260   0.00548  -0.1425   0.3814   0.5532
   5.500   1.2370   0.01270   0.00568  -0.1420   0.3781   0.5777
   5.750   1.2615   0.01280   0.00588  -0.1414   0.3743   0.6055
   6.000   1.2848   0.01291   0.00610  -0.1406   0.3702   0.6390
   6.250   1.3069   0.01305   0.00634  -0.1396   0.3663   0.6807
   6.500   1.3292   0.01316   0.00660  -0.1386   0.3628   0.7319
   6.750   1.3503   0.01319   0.00685  -0.1372   0.3590   0.8045
   7.000   1.3640   0.01309   0.00700  -0.1342   0.3551   1.0000
   7.250   1.3856   0.01334   0.00724  -0.1332   0.3509   1.0000
   7.500   1.4072   0.01361   0.00750  -0.1321   0.3470   1.0000
   7.750   1.4300   0.01382   0.00775  -0.1313   0.3429   1.0000
   8.000   1.4514   0.01408   0.00803  -0.1302   0.3383   1.0000
   8.250   1.4710   0.01440   0.00833  -0.1289   0.3337   1.0000
   8.500   1.4919   0.01468   0.00863  -0.1278   0.3294   1.0000
   8.750   1.5127   0.01496   0.00895  -0.1267   0.3242   1.0000
   9.000   1.5309   0.01532   0.00931  -0.1252   0.3187   1.0000
   9.250   1.5497   0.01568   0.00968  -0.1238   0.3135   1.0000
   9.500   1.5686   0.01604   0.01006  -0.1225   0.3073   1.0000
   9.750   1.5841   0.01652   0.01054  -0.1206   0.3012   1.0000
  10.000   1.6024   0.01691   0.01097  -0.1193   0.2954   1.0000
  10.250   1.6181   0.01740   0.01148  -0.1176   0.2889   1.0000
  10.500   1.6327   0.01797   0.01204  -0.1158   0.2828   1.0000
  10.750   1.6478   0.01852   0.01262  -0.1141   0.2757   1.0000
  11.000   1.6592   0.01925   0.01335  -0.1120   0.2684   1.0000
  11.250   1.6718   0.01996   0.01408  -0.1101   0.2594   1.0000
  11.500   1.6808   0.02087   0.01498  -0.1079   0.2499   1.0000
  11.750   1.6874   0.02196   0.01605  -0.1055   0.2398   1.0000
  12.000   1.6944   0.02310   0.01718  -0.1034   0.2285   1.0000
  12.250   1.6995   0.02441   0.01849  -0.1011   0.2182   1.0000
  12.500   1.7009   0.02604   0.02009  -0.0988   0.2065   1.0000
  12.750   1.7015   0.02783   0.02185  -0.0966   0.1954   1.0000
  13.000   1.7045   0.02955   0.02360  -0.0948   0.1858   1.0000
  13.250   1.7043   0.03161   0.02566  -0.0930   0.1767   1.0000
  13.500   1.7016   0.03400   0.02805  -0.0913   0.1670   1.0000
  13.750   1.6992   0.03650   0.03056  -0.0898   0.1569   1.0000
  14.000   1.6959   0.03921   0.03329  -0.0885   0.1488   1.0000
  14.250   1.6897   0.04232   0.03641  -0.0874   0.1401   1.0000
  14.500   1.6852   0.04541   0.03954  -0.0866   0.1321   1.0000
  14.750   1.6777   0.04894   0.04309  -0.0859   0.1246   1.0000
  15.000   1.6708   0.05254   0.04673  -0.0855   0.1171   1.0000
  15.250   1.6627   0.05643   0.05065  -0.0852   0.1105   1.0000
  15.500   1.6534   0.06060   0.05486  -0.0852   0.1037   1.0000
  15.750   1.6447   0.06481   0.05912  -0.0853   0.0972   1.0000
  16.000   1.6333   0.06951   0.06385  -0.0857   0.0907   1.0000
  16.250   1.6267   0.07370   0.06810  -0.0862   0.0856   1.0000
  16.500   1.6158   0.07856   0.07299  -0.0869   0.0800   1.0000
  16.750   1.6080   0.08309   0.07758  -0.0877   0.0748   1.0000
  17.000   1.5978   0.08808   0.08261  -0.0888   0.0699   1.0000
  17.250   1.5907   0.09267   0.08726  -0.0898   0.0652   1.0000
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