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GOE 523 AIRFOIL (goe523-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 523 AIRFOIL (goe523-il)
Reynolds number: 100,000
Max Cl/Cd: 50.85 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe523-il-100000-n5.txt
Download as CSV file: xf-goe523-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 523 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1759   0.11221   0.10684  -0.1195   0.8691   0.0729
  -9.250   0.1890   0.10932   0.10393  -0.1221   0.8660   0.0751
  -9.000   0.1835   0.10801   0.10265  -0.1226   0.8585   0.0768
  -8.750   0.1766   0.10667   0.10133  -0.1235   0.8509   0.0774
  -8.250   0.2029   0.10045   0.09511  -0.1235   0.8411   0.0790
  -8.000   0.2165   0.09817   0.09284  -0.1229   0.8353   0.0813
  -7.750   0.2313   0.09537   0.09001  -0.1250   0.8320   0.0840
  -7.500   0.2229   0.09435   0.08904  -0.1225   0.8217   0.0855
  -7.250   0.2168   0.09253   0.08722  -0.1244   0.8151   0.0875
  -6.250   0.1919   0.08082   0.07549  -0.1188   0.7812   0.0596
  -6.000   0.2064   0.07712   0.07175  -0.1216   0.7780   0.0594
  -5.500   0.1876   0.07398   0.06866  -0.1167   0.7555   0.0591
  -5.250   0.1915   0.07129   0.06597  -0.1174   0.7476   0.0587
  -4.750   0.3108   0.03967   0.03322  -0.1827   0.7362   0.0537
  -4.500   0.3608   0.03710   0.03042  -0.1901   0.7319   0.0553
  -4.250   0.4386   0.03282   0.02545  -0.2042   0.7298   0.0570
  -4.000   0.5039   0.02995   0.02197  -0.2131   0.7276   0.0582
  -3.750   0.5410   0.02878   0.02047  -0.2160   0.7204   0.0592
  -3.500   0.5820   0.02763   0.01904  -0.2190   0.7146   0.0606
  -3.250   0.6264   0.02658   0.01792  -0.2221   0.7107   0.0632
  -3.000   0.6582   0.02609   0.01730  -0.2232   0.7034   0.0659
  -2.750   0.6947   0.02543   0.01644  -0.2248   0.6969   0.0682
  -2.500   0.7404   0.02450   0.01550  -0.2280   0.6926   0.0713
  -2.250   0.7680   0.02434   0.01528  -0.2283   0.6843   0.0747
  -2.000   0.8073   0.02382   0.01471  -0.2305   0.6780   0.0813
  -1.750   0.8515   0.02323   0.01405  -0.2335   0.6725   0.0921
  -1.500   0.8797   0.02316   0.01400  -0.2340   0.6639   0.1062
  -1.250   0.9245   0.02267   0.01348  -0.2372   0.6580   0.1453
  -1.000   0.9568   0.02256   0.01346  -0.2385   0.6504   0.1889
  -0.750   0.9912   0.02246   0.01347  -0.2401   0.6428   0.2495
  -0.500   1.0313   0.02232   0.01335  -0.2424   0.6364   0.3149
  -0.250   1.0531   0.02260   0.01371  -0.2415   0.6280   0.3557
   0.000   1.0880   0.02264   0.01370  -0.2426   0.6215   0.3976
   0.250   1.1114   0.02294   0.01400  -0.2418   0.6137   0.4263
   0.500   1.1365   0.02320   0.01420  -0.2413   0.6060   0.4524
   0.750   1.1695   0.02333   0.01421  -0.2421   0.5997   0.4763
   1.000   1.1849   0.02382   0.01471  -0.2400   0.5912   0.4951
   1.250   1.2130   0.02404   0.01483  -0.2399   0.5844   0.5156
   1.500   1.2340   0.02444   0.01519  -0.2387   0.5770   0.5346
   1.750   1.2533   0.02487   0.01559  -0.2372   0.5693   0.5538
   2.250   1.2946   0.02567   0.01633  -0.2347   0.5551   0.5886
   2.500   1.3169   0.02600   0.01660  -0.2338   0.5483   0.6029
   2.750   1.3389   0.02638   0.01692  -0.2329   0.5416   0.6154
   3.000   1.3554   0.02691   0.01743  -0.2312   0.5339   0.6276
   3.250   1.3807   0.02715   0.01756  -0.2308   0.5280   0.6385
   3.500   1.3954   0.02776   0.01819  -0.2290   0.5207   0.6492
   3.750   1.4139   0.02822   0.01861  -0.2276   0.5138   0.6597
   4.000   1.4379   0.02852   0.01881  -0.2271   0.5080   0.6703
   4.250   1.4505   0.02926   0.01958  -0.2250   0.5007   0.6808
   4.500   1.4704   0.02967   0.01995  -0.2239   0.4946   0.6905
   4.750   1.4897   0.03018   0.02041  -0.2229   0.4886   0.7009
   5.000   1.5033   0.03090   0.02116  -0.2210   0.4818   0.7114
   5.250   1.5241   0.03131   0.02152  -0.2201   0.4762   0.7229
   5.500   1.5406   0.03195   0.02217  -0.2187   0.4703   0.7350
   5.750   1.5540   0.03274   0.02300  -0.2169   0.4640   0.7476
   6.000   1.5742   0.03319   0.02341  -0.2160   0.4588   0.7605
   6.250   1.5917   0.03382   0.02406  -0.2149   0.4536   0.7724
   6.500   1.6028   0.03476   0.02509  -0.2129   0.4476   0.7846
   6.750   1.6202   0.03537   0.02571  -0.2118   0.4425   0.7999
   7.000   1.6428   0.03567   0.02601  -0.2112   0.4381   0.8230
   7.250   1.6443   0.03681   0.02736  -0.2080   0.4323   1.0000
   7.500   1.6587   0.03784   0.02838  -0.2068   0.4269   1.0000
   7.750   1.6818   0.03840   0.02886  -0.2065   0.4225   1.0000
   8.000   1.6947   0.03956   0.03006  -0.2052   0.4176   1.0000
   8.250   1.7029   0.04100   0.03159  -0.2033   0.4124   1.0000
   8.500   1.7183   0.04201   0.03260  -0.2022   0.4078   1.0000
   8.750   1.7425   0.04249   0.03300  -0.2021   0.4040   1.0000
   9.000   1.7467   0.04424   0.03487  -0.2000   0.3990   1.0000
   9.250   1.7518   0.04596   0.03669  -0.1980   0.3937   1.0000
   9.500   1.7656   0.04708   0.03782  -0.1968   0.3892   1.0000
   9.750   1.7912   0.04741   0.03806  -0.1968   0.3856   1.0000
  10.000   1.7838   0.05014   0.04100  -0.1939   0.3802   1.0000
  10.250   1.7867   0.05217   0.04315  -0.1920   0.3754   1.0000
  10.500   1.8002   0.05340   0.04440  -0.1910   0.3714   1.0000
  10.750   1.8242   0.05380   0.04474  -0.1908   0.3683   1.0000
  11.000   1.8134   0.05716   0.04832  -0.1881   0.3634   1.0000
  11.250   1.8099   0.06001   0.05133  -0.1861   0.3587   1.0000
  11.500   1.8197   0.06165   0.05303  -0.1851   0.3549   1.0000
  11.750   1.8405   0.06225   0.05361  -0.1847   0.3518   1.0000
  12.000   1.8301   0.06597   0.05751  -0.1827   0.3471   1.0000
  12.250   1.8124   0.07064   0.06239  -0.1806   0.3417   1.0000
  12.500   1.8210   0.07246   0.06427  -0.1798   0.3376   1.0000
  12.750   1.8457   0.07244   0.06420  -0.1795   0.3344   1.0000
  13.000   1.8006   0.08084   0.07293  -0.1773   0.3281   1.0000
  13.250   1.7856   0.08589   0.07814  -0.1764   0.3229   1.0000
  13.500   1.8035   0.08659   0.07885  -0.1760   0.3198   1.0000
  13.750   1.8330   0.08577   0.07801  -0.1757   0.3175   1.0000
  14.000   1.7022   0.10813   0.10091  -0.1762   0.3056   1.0000
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