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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 100,000
Max Cl/Cd: 39.8 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e561-il-100000.txt
Download as CSV file: xf-e561-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6051   0.06415   0.05939  -0.0708   1.0000   0.0614
 -10.000  -0.6382   0.06229   0.05760  -0.0680   1.0000   0.0611
  -9.750  -0.6716   0.05888   0.05415  -0.0688   1.0000   0.0606
  -9.500  -0.6809   0.05248   0.04730  -0.0773   0.9945   0.0606
  -9.250  -0.6581   0.04580   0.03976  -0.0883   0.9840   0.0616
  -9.000  -0.6272   0.04247   0.03631  -0.0923   0.9756   0.0632
  -8.750  -0.5923   0.03986   0.03351  -0.0964   0.9673   0.0654
  -8.500  -0.5531   0.03712   0.03044  -0.1010   0.9601   0.0684
  -8.250  -0.5205   0.03471   0.02780  -0.1037   0.9505   0.0720
  -8.000  -0.4836   0.03310   0.02615  -0.1067   0.9419   0.0784
  -7.750  -0.4425   0.03126   0.02430  -0.1106   0.9344   0.0890
  -7.500  -0.4088   0.02943   0.02252  -0.1131   0.9244   0.1058
  -7.250  -0.3600   0.02804   0.02115  -0.1185   0.9183   0.1429
  -7.000  -0.3268   0.02786   0.02111  -0.1201   0.9069   0.1668
  -6.750  -0.2759   0.02800   0.02123  -0.1243   0.9018   0.1937
  -6.500  -0.2452   0.02871   0.02206  -0.1244   0.8896   0.2124
  -6.250  -0.1947   0.02885   0.02221  -0.1277   0.8855   0.2325
  -6.000  -0.1650   0.02868   0.02201  -0.1278   0.8737   0.2451
  -5.750  -0.1137   0.02819   0.02144  -0.1315   0.8698   0.2612
  -5.500  -0.0802   0.02771   0.02079  -0.1326   0.8590   0.2746
  -5.250  -0.0293   0.02704   0.01995  -0.1365   0.8539   0.2902
  -5.000   0.0061   0.02704   0.02005  -0.1370   0.8444   0.2999
  -4.750   0.0511   0.02634   0.01920  -0.1399   0.8371   0.3127
  -4.500   0.0882   0.02568   0.01830  -0.1418   0.8271   0.3257
  -4.250   0.1294   0.02537   0.01800  -0.1434   0.8187   0.3360
  -4.000   0.1605   0.02493   0.01741  -0.1441   0.8072   0.3466
  -3.750   0.2046   0.02429   0.01647  -0.1471   0.7992   0.3604
  -3.500   0.2286   0.02426   0.01653  -0.1459   0.7865   0.3676
  -3.250   0.2636   0.02380   0.01583  -0.1474   0.7767   0.3799
  -3.000   0.2931   0.02368   0.01571  -0.1472   0.7661   0.3886
  -2.750   0.3213   0.02342   0.01528  -0.1475   0.7551   0.3994
  -2.500   0.3556   0.02320   0.01496  -0.1483   0.7463   0.4097
  -2.250   0.3792   0.02311   0.01479  -0.1476   0.7347   0.4194
  -2.000   0.4143   0.02290   0.01440  -0.1488   0.7269   0.4311
  -1.750   0.4360   0.02291   0.01443  -0.1476   0.7157   0.4397
  -1.500   0.4687   0.02277   0.01409  -0.1485   0.7076   0.4524
  -1.250   0.4918   0.02279   0.01417  -0.1475   0.6974   0.4608
  -1.000   0.5230   0.02270   0.01393  -0.1481   0.6898   0.4728
  -0.750   0.5464   0.02280   0.01405  -0.1473   0.6804   0.4832
  -0.500   0.5792   0.02270   0.01383  -0.1480   0.6738   0.4947
  -0.250   0.6009   0.02289   0.01400  -0.1471   0.6640   0.5068
   0.000   0.6322   0.02282   0.01389  -0.1474   0.6576   0.5183
   0.250   0.6531   0.02307   0.01419  -0.1464   0.6489   0.5294
   0.500   0.6831   0.02310   0.01413  -0.1467   0.6421   0.5434
   0.750   0.7077   0.02328   0.01436  -0.1461   0.6351   0.5554
   1.000   0.7318   0.02344   0.01456  -0.1454   0.6274   0.5681
   1.250   0.7641   0.02345   0.01448  -0.1460   0.6221   0.5834
   1.500   0.7828   0.02388   0.01502  -0.1447   0.6143   0.5978
   1.750   0.8100   0.02401   0.01514  -0.1445   0.6080   0.6141
   2.000   0.8401   0.02411   0.01522  -0.1447   0.6028   0.6318
   2.250   0.8563   0.02459   0.01588  -0.1429   0.5952   0.6481
   2.500   0.8841   0.02472   0.01602  -0.1428   0.5898   0.6691
   2.750   0.9106   0.02490   0.01625  -0.1423   0.5848   0.6914
   3.000   0.9253   0.02542   0.01698  -0.1402   0.5775   0.7154
   3.250   0.9507   0.02551   0.01713  -0.1395   0.5723   0.7471
   3.500   0.9764   0.02557   0.01725  -0.1386   0.5682   0.7890
   3.750   0.9776   0.02615   0.01818  -0.1339   0.5614   0.8434
   4.000   1.0033   0.02607   0.01818  -0.1335   0.5559   1.0000
   4.250   1.0468   0.02630   0.01814  -0.1367   0.5516   1.0000
   4.500   1.0574   0.02754   0.01950  -0.1349   0.5445   1.0000
   4.750   1.0844   0.02806   0.01996  -0.1350   0.5390   1.0000
   5.000   1.1216   0.02821   0.01995  -0.1365   0.5348   1.0000
   5.250   1.1294   0.02957   0.02144  -0.1341   0.5282   1.0000
   5.500   1.1514   0.03028   0.02217  -0.1335   0.5226   1.0000
   5.750   1.1865   0.03044   0.02222  -0.1345   0.5184   1.0000
   6.000   1.1975   0.03171   0.02359  -0.1325   0.5125   1.0000
   6.250   1.2107   0.03282   0.02479  -0.1307   0.5064   1.0000
   6.500   1.2441   0.03300   0.02490  -0.1315   0.5021   1.0000
   6.750   1.2679   0.03374   0.02565  -0.1311   0.4973   1.0000
   7.000   1.2607   0.03578   0.02790  -0.1268   0.4901   1.0000
   7.250   1.2938   0.03594   0.02803  -0.1275   0.4857   1.0000
   7.500   1.3406   0.03562   0.02758  -0.1299   0.4823   1.0000
   7.750   1.2965   0.03943   0.03174  -0.1213   0.4736   1.0000
   8.000   1.3316   0.03943   0.03173  -0.1222   0.4692   1.0000
   8.250   1.3838   0.03871   0.03092  -0.1250   0.4658   1.0000
   8.500   1.2593   0.04687   0.03947  -0.1086   0.4547   1.0000
   8.750   1.3360   0.04437   0.03693  -0.1132   0.4520   1.0000
   9.000   1.4156   0.04228   0.03475  -0.1189   0.4491   1.0000
   9.250   1.1970   0.05916   0.05197  -0.0998   0.4326   1.0000
   9.500   1.2945   0.05296   0.04576  -0.1022   0.4331   1.0000
   9.750   1.4170   0.04708   0.03982  -0.1096   0.4321   1.0000
  10.000   0.9511   0.10044   0.09346  -0.1027   0.3858   1.0000
  10.250   0.9888   0.09927   0.09233  -0.1017   0.3828   1.0000
  10.500   1.0383   0.09646   0.08954  -0.1002   0.3812   1.0000
  10.750   0.9753   0.10853   0.10169  -0.1030   0.3677   1.0000
  11.000   1.0199   0.10629   0.09948  -0.1015   0.3653   1.0000
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