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GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 364 AIRFOIL (goe364-il)
Reynolds number: 100,000
Max Cl/Cd: 57.02 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe364-il-100000-n5.txt
Download as CSV file: xf-goe364-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 364 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.1429   0.10007   0.09554  -0.0505   0.9725   0.0433
  -8.250  -0.1274   0.09682   0.09230  -0.0564   0.9620   0.0451
  -8.000  -0.1179   0.09437   0.08986  -0.0661   0.9463   0.0459
  -7.750  -0.0963   0.08937   0.08488  -0.0647   0.9398   0.0471
  -7.500  -0.0740   0.08569   0.08118  -0.0677   0.9312   0.0494
  -7.250  -0.0596   0.08253   0.07801  -0.0715   0.9155   0.0517
  -7.000  -0.0458   0.07960   0.07503  -0.0796   0.8955   0.0541
  -6.750  -0.0253   0.07620   0.07151  -0.0903   0.8775   0.0548
  -6.500  -0.0084   0.07181   0.06714  -0.0866   0.8693   0.0561
  -6.250   0.0097   0.06884   0.06413  -0.0878   0.8571   0.0583
  -5.750   0.0529   0.06221   0.05723  -0.0994   0.8337   0.0660
  -5.500   0.0690   0.05943   0.05443  -0.0987   0.8239   0.0679
  -5.250   0.0883   0.05681   0.05172  -0.1003   0.8136   0.0709
  -5.000   0.1229   0.05412   0.04853  -0.1089   0.8037   0.0772
  -4.750   0.1343   0.05086   0.04540  -0.1070   0.7938   0.0788
  -4.500   0.1542   0.04862   0.04310  -0.1070   0.7856   0.0830
  -4.250   0.1826   0.04639   0.04046  -0.1108   0.7752   0.0913
  -4.000   0.2015   0.04362   0.03768  -0.1105   0.7672   0.0931
  -3.750   0.2219   0.04151   0.03547  -0.1105   0.7579   0.0957
  -3.500   0.2572   0.03655   0.02973  -0.1129   0.7510   0.0659
  -3.250   0.2785   0.03458   0.02768  -0.1124   0.7416   0.0621
  -3.000   0.3080   0.03126   0.02364  -0.1124   0.7347   0.0543
  -2.750   0.3303   0.02958   0.02180  -0.1118   0.7251   0.0535
  -2.500   0.3571   0.02789   0.01970  -0.1115   0.7178   0.0537
  -2.250   0.3815   0.02655   0.01799  -0.1107   0.7086   0.0544
  -2.000   0.4083   0.02520   0.01634  -0.1103   0.7015   0.0540
  -1.750   0.4324   0.02412   0.01503  -0.1094   0.6919   0.0538
  -1.500   0.4596   0.02309   0.01369  -0.1090   0.6842   0.0537
  -1.250   0.4844   0.02228   0.01265  -0.1081   0.6745   0.0539
  -1.000   0.5114   0.02156   0.01168  -0.1075   0.6665   0.0551
  -0.750   0.5363   0.02093   0.01099  -0.1069   0.6571   0.0566
  -0.500   0.5628   0.02036   0.01028  -0.1063   0.6490   0.0572
  -0.250   0.5881   0.01989   0.00972  -0.1055   0.6396   0.0578
   0.000   0.6137   0.01947   0.00923  -0.1048   0.6307   0.0586
   0.250   0.6390   0.01912   0.00882  -0.1040   0.6217   0.0597
   0.500   0.6639   0.01887   0.00853  -0.1032   0.6128   0.0616
   0.750   0.6895   0.01869   0.00824  -0.1025   0.6043   0.0646
   1.000   0.7141   0.01852   0.00807  -0.1018   0.5943   0.0676
   1.250   0.7407   0.01840   0.00781  -0.1012   0.5854   0.0709
   1.500   0.7651   0.01837   0.00771  -0.1004   0.5737   0.0753
   1.750   0.7898   0.01831   0.00760  -0.0996   0.5619   0.0835
   2.000   0.8150   0.01819   0.00750  -0.0989   0.5505   0.1237
   2.500   0.8870   0.01684   0.00764  -0.1024   0.5283   1.0000
   2.750   0.9113   0.01706   0.00767  -0.1016   0.5203   1.0000
   3.000   0.9344   0.01731   0.00784  -0.1007   0.5112   1.0000
   3.250   0.9583   0.01756   0.00795  -0.0998   0.5033   1.0000
   3.500   0.9812   0.01783   0.00815  -0.0989   0.4945   1.0000
   3.750   1.0047   0.01809   0.00830  -0.0980   0.4865   1.0000
   4.000   1.0274   0.01838   0.00853  -0.0970   0.4781   1.0000
   4.250   1.0507   0.01868   0.00875  -0.0962   0.4707   1.0000
   4.500   1.0730   0.01900   0.00904  -0.0952   0.4625   1.0000
   4.750   1.0961   0.01932   0.00926  -0.0943   0.4551   1.0000
   5.000   1.1175   0.01966   0.00962  -0.0932   0.4463   1.0000
   5.250   1.1399   0.02000   0.00988  -0.0923   0.4386   1.0000
   5.500   1.1606   0.02037   0.01026  -0.0911   0.4297   1.0000
   5.750   1.1826   0.02074   0.01058  -0.0901   0.4221   1.0000
   6.000   1.2026   0.02114   0.01102  -0.0889   0.4134   1.0000
   6.250   1.2236   0.02154   0.01137  -0.0878   0.4055   1.0000
   6.500   1.2423   0.02195   0.01184  -0.0863   0.3960   1.0000
   6.750   1.2616   0.02238   0.01226  -0.0850   0.3874   1.0000
   7.000   1.2796   0.02282   0.01274  -0.0835   0.3781   1.0000
   7.250   1.2972   0.02328   0.01324  -0.0819   0.3691   1.0000
   7.500   1.3143   0.02374   0.01371  -0.0803   0.3602   1.0000
   7.750   1.3297   0.02426   0.01429  -0.0784   0.3505   1.0000
   8.000   1.3454   0.02476   0.01476  -0.0766   0.3422   1.0000
   8.250   1.3585   0.02531   0.01540  -0.0744   0.3327   1.0000
   8.500   1.3715   0.02587   0.01599  -0.0723   0.3248   1.0000
   8.750   1.3830   0.02649   0.01664  -0.0699   0.3161   1.0000
   9.000   1.3945   0.02715   0.01733  -0.0677   0.3081   1.0000
   9.250   1.4051   0.02786   0.01805  -0.0654   0.3002   1.0000
   9.500   1.4156   0.02863   0.01887  -0.0633   0.2925   1.0000
   9.750   1.4253   0.02945   0.01972  -0.0612   0.2852   1.0000
  10.000   1.4354   0.03034   0.02064  -0.0592   0.2785   1.0000
  10.250   1.4446   0.03129   0.02166  -0.0572   0.2718   1.0000
  10.500   1.4548   0.03225   0.02259  -0.0555   0.2661   1.0000
  10.750   1.4633   0.03336   0.02386  -0.0537   0.2599   1.0000
  11.000   1.4721   0.03446   0.02499  -0.0520   0.2544   1.0000
  11.250   1.4815   0.03561   0.02619  -0.0504   0.2492   1.0000
  11.500   1.4889   0.03692   0.02764  -0.0489   0.2439   1.0000
  11.750   1.4975   0.03817   0.02895  -0.0475   0.2390   1.0000
  12.000   1.5073   0.03942   0.03024  -0.0462   0.2344   1.0000
  12.250   1.5116   0.04106   0.03206  -0.0448   0.2293   1.0000
  12.500   1.5176   0.04259   0.03369  -0.0435   0.2243   1.0000
  12.750   1.5277   0.04387   0.03496  -0.0424   0.2197   1.0000
  13.000   1.5277   0.04599   0.03731  -0.0412   0.2148   1.0000
  13.250   1.5308   0.04790   0.03936  -0.0402   0.2101   1.0000
  13.500   1.5390   0.04940   0.04090  -0.0393   0.2059   1.0000
  13.750   1.5395   0.05166   0.04333  -0.0384   0.2014   1.0000
  14.000   1.5371   0.05424   0.04610  -0.0376   0.1966   1.0000
  14.250   1.5375   0.05649   0.04842  -0.0370   0.1916   1.0000
  14.500   1.5338   0.05929   0.05137  -0.0365   0.1867   1.0000
  14.750   1.5247   0.06285   0.05514  -0.0363   0.1814   1.0000
  15.000   1.5214   0.06572   0.05805  -0.0362   0.1761   1.0000
  15.250   1.5108   0.06980   0.06232  -0.0366   0.1711   1.0000
  15.500   1.4999   0.07408   0.06677  -0.0372   0.1660   1.0000
  15.750   1.4971   0.07723   0.06994  -0.0376   0.1612   1.0000
  16.000   1.4815   0.08262   0.07557  -0.0388   0.1567   1.0000
  16.250   1.4696   0.08756   0.08067  -0.0401   0.1523   1.0000
  16.500   1.4668   0.09103   0.08417  -0.0410   0.1480   1.0000
  16.750   1.4496   0.09717   0.09053  -0.0430   0.1443   1.0000
  17.000   1.4331   0.10332   0.09686  -0.0452   0.1405   1.0000
  17.500   1.4131   0.11352   0.10725  -0.0490   0.1327   1.0000
  17.750   1.3873   0.12185   0.11577  -0.0526   0.1295   1.0000
  18.000   1.3707   0.12855   0.12260  -0.0557   0.1257   1.0000
  18.250   1.3827   0.12959   0.12361  -0.0559   0.1219   1.0000
  18.500   1.3419   0.14148   0.13573  -0.0619   0.1191   1.0000
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