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EPPLER 559 AIRFOIL (e559-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 559 AIRFOIL (e559-il)
Reynolds number: 50,000
Max Cl/Cd: 30.49 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e559-il-50000-n5.txt
Download as CSV file: xf-e559-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 559 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3834   0.10686   0.09942  -0.0512   1.0000   0.0749
 -11.250  -0.4110   0.09766   0.09033  -0.0549   1.0000   0.0763
 -11.000  -0.4601   0.08494   0.07771  -0.0607   1.0000   0.0768
 -10.750  -0.4210   0.09026   0.08310  -0.0559   1.0000   0.0806
 -10.500  -0.4515   0.08206   0.07501  -0.0588   1.0000   0.0822
 -10.250  -0.5114   0.07029   0.06328  -0.0640   1.0000   0.0817
 -10.000  -0.5584   0.06255   0.05549  -0.0663   1.0000   0.0811
  -9.750  -0.5930   0.05791   0.05082  -0.0661   1.0000   0.0810
  -9.500  -0.6193   0.05412   0.04699  -0.0659   1.0000   0.0816
  -9.250  -0.6362   0.05069   0.04348  -0.0661   1.0000   0.0833
  -9.000  -0.6481   0.04757   0.04020  -0.0658   1.0000   0.0860
  -8.750  -0.6528   0.04497   0.03749  -0.0653   1.0000   0.0898
  -8.500  -0.6503   0.04341   0.03599  -0.0644   1.0000   0.0947
  -8.250  -0.6474   0.04101   0.03339  -0.0645   1.0000   0.1019
  -8.000  -0.6311   0.03935   0.03170  -0.0659   0.9973   0.1122
  -7.750  -0.5958   0.03763   0.02990  -0.0708   0.9884   0.1296
  -7.500  -0.5593   0.03694   0.02925  -0.0746   0.9792   0.1491
  -7.250  -0.5223   0.03594   0.02801  -0.0789   0.9698   0.1722
  -7.000  -0.4863   0.03593   0.02800  -0.0812   0.9600   0.1898
  -6.500  -0.4187   0.03506   0.02684  -0.0852   0.9392   0.2208
  -6.250  -0.3811   0.03456   0.02614  -0.0877   0.9303   0.2360
  -6.000  -0.3475   0.03394   0.02529  -0.0897   0.9195   0.2505
  -5.750  -0.3155   0.03397   0.02531  -0.0902   0.9088   0.2612
  -5.500  -0.2756   0.03352   0.02470  -0.0927   0.9009   0.2740
  -5.250  -0.2452   0.03292   0.02390  -0.0938   0.8892   0.2863
  -5.000  -0.2095   0.03217   0.02287  -0.0959   0.8795   0.2996
  -4.750  -0.1735   0.03199   0.02267  -0.0970   0.8706   0.3097
  -4.500  -0.1413   0.03146   0.02198  -0.0981   0.8597   0.3205
  -4.250  -0.0993   0.03075   0.02101  -0.1009   0.8526   0.3340
  -4.000  -0.0698   0.03050   0.02072  -0.1011   0.8409   0.3430
  -3.750  -0.0288   0.02994   0.01999  -0.1034   0.8334   0.3549
  -3.500   0.0044   0.02938   0.01920  -0.1049   0.8221   0.3670
  -3.250   0.0359   0.02916   0.01896  -0.1051   0.8117   0.3755
  -3.000   0.0744   0.02860   0.01822  -0.1070   0.8030   0.3871
  -2.750   0.1039   0.02834   0.01785  -0.1073   0.7911   0.3972
  -2.500   0.1407   0.02793   0.01733  -0.1087   0.7824   0.4076
  -2.250   0.1724   0.02759   0.01681  -0.1096   0.7710   0.4192
  -2.000   0.2011   0.02744   0.01664  -0.1094   0.7598   0.4281
  -1.750   0.2385   0.02705   0.01609  -0.1109   0.7512   0.4396
  -1.500   0.2649   0.02696   0.01593  -0.1107   0.7388   0.4500
  -1.250   0.2952   0.02680   0.01570  -0.1110   0.7285   0.4602
  -1.000   0.3284   0.02659   0.01535  -0.1118   0.7188   0.4722
  -0.750   0.3539   0.02659   0.01534  -0.1113   0.7073   0.4824
  -0.500   0.3872   0.02641   0.01506  -0.1120   0.6984   0.4942
  -0.250   0.4139   0.02644   0.01502  -0.1119   0.6872   0.5063
   0.000   0.4413   0.02646   0.01501  -0.1117   0.6772   0.5179
   0.250   0.4719   0.02639   0.01489  -0.1119   0.6680   0.5304
   0.500   0.4966   0.02653   0.01501  -0.1114   0.6574   0.5431
   0.750   0.5296   0.02644   0.01485  -0.1120   0.6496   0.5581
   1.000   0.5513   0.02667   0.01512  -0.1111   0.6387   0.5716
   1.250   0.5818   0.02665   0.01507  -0.1113   0.6309   0.5872
   1.500   0.6040   0.02689   0.01538  -0.1103   0.6209   0.6028
   1.750   0.6326   0.02694   0.01544  -0.1103   0.6132   0.6208
   2.000   0.6550   0.02718   0.01576  -0.1093   0.6038   0.6398
   2.250   0.6821   0.02725   0.01587  -0.1089   0.5964   0.6616
   2.500   0.7019   0.02753   0.01629  -0.1075   0.5875   0.6845
   2.750   0.7294   0.02752   0.01633  -0.1070   0.5810   0.7138
   3.000   0.7439   0.02790   0.01690  -0.1047   0.5718   0.7462
   3.250   0.7677   0.02779   0.01690  -0.1033   0.5659   0.7926
   3.500   0.7784   0.02810   0.01745  -0.1002   0.5574   0.8672
   3.750   0.8137   0.02819   0.01748  -0.1017   0.5504   1.0000
   4.000   0.8371   0.02891   0.01814  -0.1017   0.5422   1.0000
   4.250   0.8652   0.02941   0.01855  -0.1022   0.5352   1.0000
   4.500   0.8921   0.02996   0.01903  -0.1024   0.5287   1.0000
   4.750   0.9120   0.03076   0.01983  -0.1016   0.5208   1.0000
   5.000   0.9455   0.03101   0.01999  -0.1025   0.5155   1.0000
   5.250   0.9571   0.03218   0.02124  -0.1007   0.5072   1.0000
   5.500   0.9842   0.03268   0.02170  -0.1007   0.5012   1.0000
   5.750   1.0050   0.03348   0.02251  -0.1000   0.4947   1.0000
   6.000   1.0207   0.03449   0.02360  -0.0988   0.4875   1.0000
   6.250   1.0531   0.03476   0.02383  -0.0993   0.4826   1.0000
   6.500   1.0575   0.03632   0.02551  -0.0968   0.4747   1.0000
   6.750   1.0803   0.03700   0.02624  -0.0963   0.4687   1.0000
   7.000   1.1076   0.03753   0.02676  -0.0962   0.4637   1.0000
   7.250   1.1039   0.03950   0.02890  -0.0930   0.4556   1.0000
   7.500   1.1343   0.03979   0.02920  -0.0932   0.4505   1.0000
   7.750   1.1315   0.04176   0.03131  -0.0901   0.4433   1.0000
   8.000   1.1392   0.04313   0.03276  -0.0880   0.4368   1.0000
   8.250   1.1828   0.04281   0.03244  -0.0895   0.4326   1.0000
   8.500   1.1357   0.04720   0.03702  -0.0828   0.4230   1.0000
   8.750   1.1667   0.04732   0.03718  -0.0828   0.4182   1.0000
   9.000   1.1215   0.05269   0.04269  -0.0784   0.4082   1.0000
   9.250   1.1413   0.05348   0.04356  -0.0776   0.4027   1.0000
   9.500   1.1949   0.05173   0.04185  -0.0784   0.3997   1.0000
   9.750   1.1128   0.06135   0.05160  -0.0749   0.3859   1.0000
  10.000   1.1623   0.05915   0.04948  -0.0744   0.3836   1.0000
  10.250   1.0940   0.06951   0.05993  -0.0742   0.3688   1.0000
  10.750   1.0550   0.08142   0.07199  -0.0755   0.3476   1.0000
  11.250   1.0806   0.08456   0.07531  -0.0746   0.3356   1.0000
  11.750   1.0313   0.09886   0.08975  -0.0779   0.3121   1.0000
  12.000   1.0474   0.09998   0.09097  -0.0774   0.3064   1.0000
  12.250   1.0786   0.09876   0.08987  -0.0760   0.3035   1.0000
  12.750   1.0365   0.11258   0.10383  -0.0801   0.2809   1.0000
  13.000   1.0521   0.11374   0.10509  -0.0797   0.2752   1.0000
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