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EPPLER 561 AIRFOIL (e561-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 561 AIRFOIL (e561-il)
Reynolds number: 50,000
Max Cl/Cd: 26.89 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e561-il-50000-n5.txt
Download as CSV file: xf-e561-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3229   0.10569   0.09874  -0.0531   1.0000   0.0672
 -10.500  -0.3421   0.09980   0.09298  -0.0544   1.0000   0.0686
 -10.250  -0.3761   0.09148   0.08479  -0.0567   1.0000   0.0694
 -10.000  -0.4184   0.08302   0.07644  -0.0588   1.0000   0.0692
  -9.750  -0.4667   0.07543   0.06893  -0.0601   1.0000   0.0687
  -9.500  -0.5080   0.07040   0.06394  -0.0596   1.0000   0.0680
  -9.250  -0.5452   0.06534   0.05884  -0.0606   0.9971   0.0675
  -9.000  -0.5521   0.05682   0.04990  -0.0724   0.9829   0.0695
  -8.750  -0.5344   0.05278   0.04577  -0.0791   0.9709   0.0736
  -8.500  -0.5187   0.04837   0.04106  -0.0854   0.9578   0.0792
  -8.250  -0.4946   0.04556   0.03821  -0.0900   0.9468   0.0868
  -8.000  -0.4721   0.04287   0.03543  -0.0939   0.9346   0.0969
  -7.750  -0.4471   0.04072   0.03320  -0.0975   0.9229   0.1110
  -7.500  -0.4173   0.03870   0.03099  -0.1017   0.9124   0.1303
  -7.250  -0.3813   0.03846   0.03085  -0.1044   0.9032   0.1506
  -7.000  -0.3525   0.03792   0.03020  -0.1060   0.8916   0.1689
  -6.750  -0.3140   0.03682   0.02880  -0.1096   0.8839   0.1888
  -6.500  -0.2848   0.03678   0.02874  -0.1099   0.8727   0.2023
  -6.250  -0.2512   0.03653   0.02839  -0.1111   0.8636   0.2161
  -6.000  -0.2167   0.03603   0.02775  -0.1125   0.8546   0.2295
  -5.750  -0.1839   0.03531   0.02681  -0.1141   0.8451   0.2427
  -5.500  -0.1464   0.03439   0.02561  -0.1165   0.8369   0.2568
  -5.250  -0.1151   0.03417   0.02529  -0.1170   0.8270   0.2674
  -5.000  -0.0776   0.03358   0.02454  -0.1188   0.8189   0.2787
  -4.750  -0.0462   0.03282   0.02352  -0.1202   0.8086   0.2912
  -4.500  -0.0096   0.03241   0.02297  -0.1215   0.8007   0.3017
  -4.250   0.0191   0.03200   0.02242  -0.1219   0.7900   0.3117
  -4.000   0.0588   0.03119   0.02129  -0.1244   0.7824   0.3250
  -3.750   0.0838   0.03116   0.02126  -0.1236   0.7712   0.3328
  -3.500   0.1232   0.03047   0.02032  -0.1259   0.7640   0.3449
  -3.250   0.1477   0.03037   0.02013  -0.1254   0.7526   0.3541
  -3.000   0.1865   0.02983   0.01939  -0.1272   0.7456   0.3652
  -2.750   0.2104   0.02971   0.01913  -0.1269   0.7342   0.3755
  -2.500   0.2478   0.02932   0.01861  -0.1282   0.7275   0.3858
  -2.250   0.2716   0.02921   0.01831  -0.1281   0.7160   0.3970
  -2.000   0.3056   0.02897   0.01801  -0.1287   0.7091   0.4064
  -1.750   0.3288   0.02897   0.01789  -0.1283   0.6984   0.4171
  -1.500   0.3645   0.02870   0.01750  -0.1294   0.6920   0.4280
  -1.250   0.3849   0.02885   0.01761  -0.1284   0.6812   0.4379
  -1.000   0.4208   0.02860   0.01719  -0.1297   0.6748   0.4504
  -0.750   0.4399   0.02885   0.01747  -0.1284   0.6649   0.4594
  -0.500   0.4737   0.02870   0.01718  -0.1294   0.6582   0.4723
  -0.250   0.4949   0.02895   0.01743  -0.1284   0.6492   0.4825
   0.000   0.5249   0.02894   0.01734  -0.1287   0.6422   0.4948
   0.250   0.5516   0.02909   0.01742  -0.1287   0.6348   0.5078
   0.500   0.5755   0.02930   0.01763  -0.1281   0.6270   0.5193
   0.750   0.6096   0.02919   0.01745  -0.1289   0.6217   0.5336
   1.000   0.6259   0.02973   0.01803  -0.1274   0.6127   0.5461
   1.250   0.6557   0.02980   0.01805  -0.1277   0.6067   0.5616
   1.500   0.6794   0.03009   0.01837  -0.1271   0.6001   0.5765
   1.750   0.6996   0.03049   0.01883  -0.1260   0.5927   0.5914
   2.000   0.7309   0.03048   0.01881  -0.1264   0.5877   0.6103
   2.250   0.7463   0.03111   0.01955  -0.1247   0.5803   0.6277
   2.500   0.7686   0.03144   0.01995  -0.1239   0.5740   0.6487
   2.750   0.7991   0.03138   0.01993  -0.1239   0.5696   0.6740
   3.000   0.8070   0.03226   0.02100  -0.1212   0.5619   0.6983
   3.250   0.8262   0.03255   0.02142  -0.1197   0.5562   0.7314
   3.500   0.8516   0.03239   0.02137  -0.1185   0.5522   0.7798
   3.750   0.8482   0.03334   0.02260  -0.1139   0.5447   0.8493
   4.000   0.8718   0.03374   0.02299  -0.1137   0.5388   1.0000
   4.250   0.9112   0.03389   0.02294  -0.1157   0.5348   1.0000
   4.500   0.9119   0.03569   0.02480  -0.1131   0.5268   1.0000
   4.750   0.9354   0.03644   0.02548  -0.1130   0.5213   1.0000
   5.000   0.9726   0.03655   0.02546  -0.1143   0.5176   1.0000
   5.250   0.9608   0.03894   0.02795  -0.1104   0.5091   1.0000
   5.500   0.9805   0.03982   0.02881  -0.1097   0.5039   1.0000
   5.750   1.0194   0.03983   0.02874  -0.1110   0.5005   1.0000
   6.000   0.9846   0.04349   0.03253  -0.1050   0.4906   1.0000
   6.250   1.0073   0.04423   0.03324  -0.1046   0.4859   1.0000
   6.500   1.0477   0.04399   0.03297  -0.1058   0.4831   1.0000
   6.750   0.9897   0.05000   0.03914  -0.0997   0.4705   1.0000
   7.000   1.0226   0.04997   0.03908  -0.0998   0.4673   1.0000
   7.250   1.0653   0.04931   0.03839  -0.1007   0.4652   1.0000
   7.500   0.9985   0.05732   0.04655  -0.0964   0.4506   1.0000
   7.750   1.0355   0.05671   0.04594  -0.0964   0.4485   1.0000
   8.250   1.0148   0.06475   0.05411  -0.0946   0.4316   1.0000
   8.750   0.9573   0.07817   0.06770  -0.0947   0.4079   1.0000
   9.250   0.9923   0.08077   0.07038  -0.0940   0.3988   1.0000
   9.750   0.9846   0.08864   0.07837  -0.0943   0.3833   1.0000
  10.000   1.0141   0.08846   0.07824  -0.0936   0.3810   1.0000
  10.250   0.9810   0.09615   0.08602  -0.0948   0.3685   1.0000
  10.500   1.0064   0.09647   0.08639  -0.0942   0.3655   1.0000
  10.750   0.9825   0.10315   0.09315  -0.0955   0.3546   1.0000
  11.000   1.0021   0.10418   0.09424  -0.0951   0.3505   1.0000
  11.250   1.0274   0.10447   0.09460  -0.0945   0.3477   1.0000
  11.750   1.0256   0.11193   0.10222  -0.0956   0.3330   1.0000
  12.000   1.0048   0.11854   0.10892  -0.0975   0.3227   1.0000
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