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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 200,000
Max Cl/Cd: 69.96 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e561-il-200000.txt
Download as CSV file: xf-e561-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.5578   0.07712   0.07291  -0.0768   1.0000   0.0349
 -12.750  -0.5846   0.07088   0.06658  -0.0800   1.0000   0.0347
 -12.500  -0.6111   0.06529   0.06089  -0.0825   1.0000   0.0346
 -12.250  -0.6325   0.06092   0.05644  -0.0839   1.0000   0.0344
 -12.000  -0.6575   0.05685   0.05228  -0.0847   1.0000   0.0343
 -11.750  -0.6817   0.05363   0.04901  -0.0843   1.0000   0.0341
 -11.500  -0.7083   0.05114   0.04648  -0.0826   1.0000   0.0340
 -11.250  -0.7431   0.04942   0.04475  -0.0793   1.0000   0.0339
 -11.000  -0.7263   0.04384   0.03877  -0.0912   0.9910   0.0340
 -10.750  -0.6991   0.03988   0.03443  -0.0986   0.9837   0.0343
 -10.500  -0.6720   0.03686   0.03108  -0.1033   0.9755   0.0347
 -10.250  -0.6395   0.03431   0.02830  -0.1072   0.9700   0.0352
  -9.750  -0.5758   0.03066   0.02465  -0.1120   0.9575   0.0370
  -9.500  -0.5440   0.02906   0.02297  -0.1143   0.9500   0.0381
  -9.250  -0.5093   0.02750   0.02128  -0.1170   0.9442   0.0396
  -9.000  -0.4771   0.02593   0.01966  -0.1192   0.9366   0.0411
  -8.750  -0.4369   0.02438   0.01815  -0.1231   0.9330   0.0441
  -8.500  -0.4075   0.02314   0.01678  -0.1244   0.9232   0.0469
  -8.250  -0.3674   0.02143   0.01510  -0.1282   0.9192   0.0520
  -8.000  -0.3348   0.01988   0.01353  -0.1304   0.9108   0.0608
  -7.750  -0.2947   0.01775   0.01160  -0.1347   0.9054   0.0956
  -7.500  -0.2473   0.01675   0.01064  -0.1391   0.9020   0.1319
  -7.250  -0.2113   0.01629   0.01016  -0.1410   0.8916   0.1518
  -7.000  -0.1628   0.01583   0.00959  -0.1451   0.8861   0.1706
  -6.750  -0.1253   0.01556   0.00924  -0.1470   0.8744   0.1860
  -6.500  -0.0817   0.01542   0.00897  -0.1501   0.8646   0.2038
  -6.250  -0.0422   0.01535   0.00882  -0.1523   0.8526   0.2194
  -6.000  -0.0089   0.01527   0.00871  -0.1532   0.8383   0.2315
  -5.750   0.0240   0.01515   0.00845  -0.1541   0.8243   0.2426
  -5.500   0.0566   0.01512   0.00826  -0.1549   0.8109   0.2535
  -5.000   0.1162   0.01498   0.00787  -0.1553   0.7839   0.2726
  -4.750   0.1436   0.01491   0.00781  -0.1550   0.7704   0.2804
  -4.500   0.1728   0.01488   0.00756  -0.1551   0.7580   0.2901
  -4.250   0.2012   0.01484   0.00750  -0.1550   0.7463   0.2979
  -4.000   0.2281   0.01482   0.00731  -0.1547   0.7337   0.3071
  -3.750   0.2557   0.01478   0.00727  -0.1545   0.7225   0.3146
  -3.500   0.2841   0.01481   0.00709  -0.1544   0.7114   0.3240
  -3.250   0.3102   0.01475   0.00707  -0.1539   0.6999   0.3313
  -3.000   0.3390   0.01480   0.00694  -0.1540   0.6903   0.3407
  -2.750   0.3652   0.01474   0.00690  -0.1535   0.6795   0.3481
  -2.500   0.3932   0.01480   0.00684  -0.1534   0.6700   0.3572
  -2.250   0.4202   0.01476   0.00675  -0.1532   0.6601   0.3650
  -2.000   0.4475   0.01481   0.00675  -0.1529   0.6508   0.3739
  -1.750   0.4752   0.01481   0.00667  -0.1528   0.6421   0.3825
  -1.500   0.5024   0.01486   0.00669  -0.1526   0.6335   0.3910
  -1.250   0.5299   0.01488   0.00662  -0.1524   0.6250   0.4000
  -1.000   0.5572   0.01494   0.00667  -0.1522   0.6169   0.4089
  -0.750   0.5844   0.01496   0.00663  -0.1520   0.6087   0.4180
  -0.500   0.6126   0.01506   0.00668  -0.1520   0.6019   0.4271
  -0.250   0.6391   0.01509   0.00671  -0.1516   0.5938   0.4367
   0.000   0.6676   0.01518   0.00674  -0.1517   0.5873   0.4464
   0.250   0.6937   0.01524   0.00682  -0.1513   0.5798   0.4560
   0.500   0.7212   0.01532   0.00688  -0.1512   0.5731   0.4667
   0.750   0.7496   0.01544   0.00696  -0.1512   0.5673   0.4766
   1.000   0.7757   0.01553   0.00707  -0.1509   0.5603   0.4882
   1.250   0.8031   0.01559   0.00715  -0.1507   0.5544   0.4989
   1.500   0.8307   0.01573   0.00728  -0.1507   0.5486   0.5107
   1.750   0.8569   0.01584   0.00743  -0.1503   0.5424   0.5236
   2.000   0.8845   0.01593   0.00755  -0.1502   0.5370   0.5366
   2.250   0.9121   0.01609   0.00772  -0.1502   0.5318   0.5506
   2.500   0.9374   0.01619   0.00792  -0.1497   0.5258   0.5659
   2.750   0.9647   0.01631   0.00807  -0.1496   0.5207   0.5833
   3.000   0.9937   0.01651   0.00826  -0.1498   0.5162   0.6030
   3.250   1.0172   0.01660   0.00854  -0.1489   0.5105   0.6248
   3.500   1.0429   0.01670   0.00874  -0.1485   0.5052   0.6519
   3.750   1.0702   0.01683   0.00893  -0.1483   0.5009   0.6855
   4.000   1.0936   0.01696   0.00925  -0.1474   0.4962   0.7281
   4.250   1.1129   0.01698   0.00952  -0.1455   0.4911   0.7902
   4.500   1.1267   0.01675   0.00953  -0.1420   0.4868   0.9415
   4.750   1.1596   0.01707   0.00969  -0.1432   0.4826   1.0000
   5.000   1.1840   0.01738   0.01005  -0.1428   0.4776   1.0000
   5.250   1.2098   0.01765   0.01032  -0.1425   0.4725   1.0000
   5.500   1.2381   0.01793   0.01053  -0.1427   0.4681   1.0000
   5.750   1.2669   0.01833   0.01086  -0.1431   0.4640   1.0000
   6.000   1.2887   0.01863   0.01126  -0.1421   0.4588   1.0000
   6.250   1.3141   0.01892   0.01155  -0.1418   0.4540   1.0000
   6.500   1.3427   0.01923   0.01180  -0.1420   0.4499   1.0000
   6.750   1.3673   0.01964   0.01224  -0.1416   0.4454   1.0000
   7.000   1.3888   0.01998   0.01266  -0.1406   0.4403   1.0000
   7.250   1.4143   0.02028   0.01296  -0.1402   0.4357   1.0000
   7.500   1.4440   0.02064   0.01323  -0.1407   0.4316   1.0000
   7.750   1.4628   0.02105   0.01378  -0.1393   0.4267   1.0000
   8.000   1.4842   0.02140   0.01420  -0.1382   0.4217   1.0000
   8.250   1.5104   0.02169   0.01446  -0.1381   0.4172   1.0000
   8.500   1.5361   0.02213   0.01489  -0.1379   0.4127   1.0000
   8.750   1.5519   0.02253   0.01545  -0.1359   0.4074   1.0000
   9.000   1.5741   0.02283   0.01578  -0.1350   0.4024   1.0000
   9.250   1.6034   0.02317   0.01603  -0.1354   0.3978   1.0000
   9.500   1.6155   0.02363   0.01668  -0.1329   0.3925   1.0000
   9.750   1.6331   0.02396   0.01708  -0.1313   0.3870   1.0000
  10.000   1.6591   0.02422   0.01728  -0.1311   0.3820   1.0000
  10.250   1.6710   0.02472   0.01792  -0.1286   0.3766   1.0000
  10.500   1.6838   0.02508   0.01837  -0.1262   0.3708   1.0000
  10.750   1.7064   0.02533   0.01857  -0.1254   0.3656   1.0000
  11.000   1.7125   0.02586   0.01924  -0.1219   0.3602   1.0000
  11.250   1.7197   0.02630   0.01978  -0.1187   0.3545   1.0000
  11.500   1.7394   0.02660   0.02003  -0.1175   0.3491   1.0000
  11.750   1.7409   0.02730   0.02089  -0.1136   0.3435   1.0000
  12.000   1.7462   0.02788   0.02157  -0.1105   0.3375   1.0000
  12.250   1.7650   0.02827   0.02188  -0.1093   0.3316   1.0000
  12.500   1.7582   0.02933   0.02316  -0.1048   0.3256   1.0000
  12.750   1.7636   0.03008   0.02397  -0.1021   0.3194   1.0000
  13.000   1.7688   0.03102   0.02496  -0.0996   0.3131   1.0000
  13.250   1.7659   0.03232   0.02639  -0.0965   0.3064   1.0000
  13.500   1.7747   0.03321   0.02724  -0.0946   0.2997   1.0000
  13.750   1.7658   0.03510   0.02933  -0.0915   0.2926   1.0000
  14.000   1.7705   0.03635   0.03052  -0.0897   0.2853   1.0000
  14.250   1.7610   0.03869   0.03307  -0.0872   0.2778   1.0000
  14.500   1.7616   0.04045   0.03478  -0.0856   0.2701   1.0000
  14.750   1.7519   0.04324   0.03776  -0.0838   0.2622   1.0000
  15.000   1.7501   0.04545   0.03992  -0.0825   0.2541   1.0000
  15.250   1.7387   0.04883   0.04348  -0.0814   0.2457   1.0000
  15.500   1.7332   0.05175   0.04639  -0.0805   0.2375   1.0000
  15.750   1.7223   0.05546   0.05022  -0.0799   0.2286   1.0000
  16.000   1.7130   0.05918   0.05398  -0.0796   0.2201   1.0000
  16.250   1.7026   0.06315   0.05797  -0.0795   0.2113   1.0000
  16.500   1.6913   0.06751   0.06243  -0.0797   0.2027   1.0000
  16.750   1.6808   0.07176   0.06665  -0.0800   0.1942   1.0000
  17.000   1.6675   0.07671   0.07171  -0.0807   0.1852   1.0000
  17.250   1.6559   0.08148   0.07651  -0.0815   0.1768   1.0000
  17.500   1.6430   0.08654   0.08160  -0.0825   0.1683   1.0000
  17.750   1.6309   0.09167   0.08681  -0.0837   0.1599   1.0000
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