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EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 560 AIRFOIL (e560-il)
Reynolds number: 50,000
Max Cl/Cd: 7.82 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e560-il-50000.txt
Download as CSV file: xf-e560-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 560 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.2734   0.13093   0.12394  -0.0338   1.0000   0.2505
 -10.000  -0.2528   0.12558   0.11859  -0.0325   1.0000   0.2586
  -9.750  -0.2687   0.12516   0.11829  -0.0318   1.0000   0.2664
  -9.500  -0.2543   0.12071   0.11385  -0.0304   1.0000   0.2752
  -9.250  -0.2729   0.12052   0.11379  -0.0292   1.0000   0.2829
  -9.000  -0.2589   0.11638   0.10966  -0.0275   1.0000   0.2944
  -8.750  -0.2851   0.11683   0.11027  -0.0257   1.0000   0.3000
  -8.500  -0.2694   0.11270   0.10614  -0.0238   1.0000   0.3128
  -8.250  -0.3022   0.11368   0.10731  -0.0211   1.0000   0.3171
  -8.000  -0.2849   0.10959   0.10321  -0.0191   1.0000   0.3305
  -7.750  -0.3196   0.11066   0.10447  -0.0159   1.0000   0.3340
  -7.500  -0.3022   0.10676   0.10054  -0.0139   1.0000   0.3470
  -7.250  -0.3374   0.10775   0.10172  -0.0104   1.0000   0.3509
  -7.000  -0.3219   0.10403   0.09797  -0.0086   1.0000   0.3608
  -6.750  -0.3511   0.10450   0.09858  -0.0052   1.0000   0.3673
  -6.500  -0.3493   0.10194   0.09606  -0.0032   1.0000   0.3750
  -6.250  -0.3694   0.10171   0.09592   0.0000   1.0000   0.3837
  -6.000  -0.4971   0.09111   0.08564  -0.0115   1.0000   0.2674
  -5.750  -0.4907   0.09112   0.08566  -0.0069   1.0000   0.2828
  -5.500  -0.4968   0.08757   0.08210  -0.0073   1.0000   0.2810
  -5.250  -0.5031   0.08316   0.07769  -0.0098   0.9997   0.2789
  -5.000  -0.4432   0.08788   0.08230  -0.0043   0.9869   0.3426
  -4.750  -0.4412   0.07090   0.06497  -0.0329   0.9775   0.2972
  -4.500  -0.4080   0.06852   0.06243  -0.0375   0.9661   0.3113
  -4.250  -0.3737   0.06528   0.05898  -0.0441   0.9547   0.3251
  -4.000  -0.3346   0.06161   0.05504  -0.0523   0.9438   0.3394
  -3.750  -0.2915   0.05909   0.05226  -0.0592   0.9330   0.3557
  -3.500  -0.2527   0.05644   0.04932  -0.0659   0.9212   0.3710
  -3.250  -0.2129   0.05431   0.04689  -0.0723   0.9099   0.3867
  -3.000  -0.1883   0.05450   0.04710  -0.0707   0.8988   0.3974
  -2.750  -0.1448   0.05317   0.04558  -0.0756   0.8883   0.4126
  -2.500  -0.1137   0.05195   0.04415  -0.0791   0.8767   0.4257
  -2.250  -0.0733   0.05088   0.04284  -0.0839   0.8660   0.4407
  -2.000  -0.0278   0.05001   0.04175  -0.0886   0.8559   0.4568
  -1.750  -0.0121   0.05006   0.04182  -0.0871   0.8445   0.4657
  -1.500   0.0272   0.04948   0.04107  -0.0906   0.8346   0.4795
  -1.250   0.0642   0.04902   0.04044  -0.0937   0.8242   0.4939
  -1.000   0.0903   0.04899   0.04029  -0.0953   0.8135   0.5061
  -0.750   0.1359   0.04856   0.03976  -0.0984   0.8051   0.5216
  -0.500   0.1492   0.04896   0.04011  -0.0978   0.7937   0.5310
  -0.250   0.1858   0.04891   0.03994  -0.1003   0.7847   0.5457
   0.000   0.2143   0.04915   0.04007  -0.1020   0.7748   0.5597
   0.250   0.2325   0.04965   0.04059  -0.1013   0.7654   0.5704
   0.500   0.2650   0.04981   0.04070  -0.1028   0.7568   0.5852
   0.750   0.2816   0.05067   0.04150  -0.1029   0.7473   0.5975
   1.000   0.3182   0.05078   0.04157  -0.1047   0.7393   0.6142
   1.250   0.3277   0.05206   0.04283  -0.1041   0.7300   0.6266
   1.500   0.3638   0.05231   0.04303  -0.1057   0.7224   0.6449
   1.750   0.3678   0.05381   0.04457  -0.1041   0.7138   0.6563
   2.000   0.3975   0.05437   0.04511  -0.1050   0.7062   0.6755
   2.250   0.4074   0.05585   0.04661  -0.1043   0.6987   0.6907
   2.500   0.4236   0.05704   0.04782  -0.1042   0.6912   0.7092
   2.750   0.4500   0.05782   0.04862  -0.1045   0.6844   0.7329
   3.000   0.4460   0.06000   0.05087  -0.1030   0.6779   0.7495
   3.250   0.4737   0.06055   0.05150  -0.1030   0.6716   0.7816
   3.500   0.4729   0.06236   0.05343  -0.1011   0.6659   0.8084
   3.750   0.4689   0.06419   0.05544  -0.0990   0.6615   0.8440
   4.000   0.4759   0.06524   0.05673  -0.0982   0.6572   1.0000
   4.250   0.5212   0.06768   0.05891  -0.1054   0.6495   1.0000
   4.500   0.5301   0.07086   0.06195  -0.1078   0.6466   1.0000
   4.750   0.5393   0.07393   0.06489  -0.1094   0.6455   1.0000
   5.000   0.5463   0.07703   0.06790  -0.1105   0.6458   1.0000
   5.250   0.5569   0.08032   0.07111  -0.1119   0.6496   1.0000
   5.500   0.4827   0.08970   0.08074  -0.1136   0.7539   1.0000
   5.750   0.4829   0.09069   0.08168  -0.1124   0.7419   1.0000
   6.000   0.5109   0.09407   0.08495  -0.1146   0.7362   1.0000
   6.250   0.5209   0.09566   0.08650  -0.1143   0.7237   1.0000
   6.500   0.5312   0.09793   0.08874  -0.1144   0.7144   1.0000
   6.750   0.5619   0.10106   0.09180  -0.1164   0.7049   1.0000
   7.000   0.5624   0.10274   0.09348  -0.1155   0.6944   1.0000
   7.250   0.6023   0.10689   0.09759  -0.1182   0.6867   1.0000
   7.500   0.5973   0.10789   0.09860  -0.1168   0.6741   1.0000
   7.750   0.6172   0.11122   0.10191  -0.1179   0.6677   1.0000
   8.000   0.6314   0.11337   0.10407  -0.1181   0.6554   1.0000
   8.250   0.6356   0.11558   0.10630  -0.1178   0.6450   1.0000
   8.500   0.6690   0.11943   0.11016  -0.1196   0.6368   1.0000
   8.750   0.6639   0.12091   0.11167  -0.1187   0.6253   1.0000
   9.000   0.6956   0.12520   0.11597  -0.1205   0.6184   1.0000
   9.250   0.6961   0.12661   0.11741  -0.1199   0.6055   1.0000
   9.500   0.7025   0.12936   0.12021  -0.1201   0.5973   1.0000
   9.750   0.7287   0.13277   0.12366  -0.1212   0.5869   1.0000
  10.000   0.7257   0.13465   0.12558  -0.1209   0.5760   1.0000
  10.250   0.7636   0.13963   0.13060  -0.1227   0.5688   1.0000
  10.500   0.7518   0.14043   0.13145  -0.1220   0.5568   1.0000
  10.750   0.7666   0.14394   0.13501  -0.1227   0.5491   1.0000
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