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GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 303 (FRIEDRICHSHAFEN G03) AIRFOIL (goe303-il)
Reynolds number: 100,000
Max Cl/Cd: 58.29 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe303-il-100000.txt
Download as CSV file: xf-goe303-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 303 (FRIEDRICHSHAFEN G03) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.2838   0.09995   0.09606  -0.0174   1.0000   0.0788
  -7.250  -0.3541   0.10302   0.09877  -0.0202   1.0000   0.0766
  -7.000  -0.3558   0.10067   0.09648  -0.0175   1.0000   0.0778
  -6.750  -0.3617   0.09891   0.09479  -0.0155   1.0000   0.0790
  -6.500  -0.3684   0.09728   0.09322  -0.0141   1.0000   0.0802
  -6.250  -0.3577   0.09434   0.09029  -0.0173   0.9969   0.0828
  -6.000  -0.2933   0.08962   0.08530  -0.0472   0.9839   0.0891
  -5.750  -0.2847   0.08414   0.07994  -0.0416   0.9790   0.0907
  -5.500  -0.2591   0.08029   0.07609  -0.0429   0.9732   0.0946
  -5.250  -0.1934   0.07652   0.07190  -0.0663   0.9610   0.1043
  -5.000  -0.1785   0.07113   0.06665  -0.0641   0.9557   0.1059
  -4.750  -0.1547   0.06770   0.06323  -0.0650   0.9478   0.1094
  -4.500  -0.1016   0.06375   0.05894  -0.0785   0.9385   0.1211
  -4.250  -0.0784   0.06009   0.05537  -0.0783   0.9322   0.1250
  -4.000  -0.0303   0.05674   0.05170  -0.0878   0.9234   0.1377
  -3.750  -0.0018   0.05336   0.04838  -0.0890   0.9169   0.1425
  -3.500   0.0425   0.05011   0.04490  -0.0955   0.9102   0.1559
  -3.250   0.0794   0.04749   0.04213  -0.0994   0.9018   0.1716
  -3.000   0.1251   0.04440   0.03894  -0.1044   0.8983   0.1891
  -2.750   0.1595   0.04358   0.03781  -0.1072   0.8870   0.2161
  -2.500   0.2001   0.03978   0.03406  -0.1108   0.8835   0.2353
  -1.750   0.3567   0.02942   0.02165  -0.1236   0.8662   0.1161
  -1.500   0.3862   0.02780   0.01971  -0.1236   0.8554   0.1108
  -1.250   0.4298   0.02602   0.01757  -0.1257   0.8507   0.1104
  -1.000   0.4579   0.02524   0.01658  -0.1254   0.8399   0.1136
  -0.750   0.4985   0.02388   0.01497  -0.1268   0.8346   0.1163
  -0.500   0.5254   0.02333   0.01422  -0.1261   0.8236   0.1198
  -0.250   0.5632   0.02213   0.01307  -0.1272   0.8182   0.1315
   0.000   0.5880   0.02167   0.01268  -0.1264   0.8068   0.1454
   0.250   0.6201   0.02079   0.01190  -0.1264   0.7996   0.1790
   0.500   0.6489   0.01990   0.01131  -0.1262   0.7899   0.2663
   0.750   0.6814   0.01800   0.01084  -0.1261   0.7804   1.0000
   1.000   0.7147   0.01769   0.01023  -0.1260   0.7714   1.0000
   1.250   0.7410   0.01765   0.01000  -0.1251   0.7580   1.0000
   1.500   0.7681   0.01759   0.00977  -0.1242   0.7448   1.0000
   1.750   0.7959   0.01758   0.00961  -0.1235   0.7330   1.0000
   2.000   0.8262   0.01755   0.00942  -0.1234   0.7237   1.0000
   2.250   0.8507   0.01784   0.00963  -0.1226   0.7119   1.0000
   2.500   0.8773   0.01805   0.00975  -0.1221   0.7014   1.0000
   2.750   0.9066   0.01812   0.00970  -0.1218   0.6917   1.0000
   3.000   0.9307   0.01842   0.00997  -0.1210   0.6795   1.0000
   3.250   0.9565   0.01866   0.01015  -0.1203   0.6681   1.0000
   3.500   0.9851   0.01878   0.01017  -0.1200   0.6579   1.0000
   3.750   1.0095   0.01906   0.01043  -0.1192   0.6456   1.0000
   4.000   1.0341   0.01935   0.01071  -0.1184   0.6334   1.0000
   4.250   1.0600   0.01957   0.01090  -0.1177   0.6214   1.0000
   4.500   1.0872   0.01971   0.01097  -0.1172   0.6094   1.0000
   4.750   1.1122   0.01992   0.01114  -0.1164   0.5957   1.0000
   5.000   1.1359   0.02016   0.01138  -0.1154   0.5810   1.0000
   5.250   1.1599   0.02041   0.01163  -0.1144   0.5660   1.0000
   5.500   1.1838   0.02067   0.01187  -0.1134   0.5505   1.0000
   5.750   1.2077   0.02094   0.01211  -0.1124   0.5343   1.0000
   6.000   1.2314   0.02123   0.01237  -0.1114   0.5174   1.0000
   6.250   1.2549   0.02155   0.01262  -0.1104   0.5000   1.0000
   6.500   1.2782   0.02193   0.01293  -0.1093   0.4827   1.0000
   6.750   1.2996   0.02242   0.01344  -0.1081   0.4655   1.0000
   7.000   1.3222   0.02295   0.01393  -0.1071   0.4499   1.0000
   7.250   1.3455   0.02349   0.01442  -0.1063   0.4358   1.0000
   7.500   1.3664   0.02410   0.01507  -0.1052   0.4220   1.0000
   7.750   1.3872   0.02473   0.01578  -0.1040   0.4091   1.0000
   8.000   1.4079   0.02531   0.01638  -0.1028   0.3965   1.0000
   8.250   1.4284   0.02582   0.01688  -0.1016   0.3838   1.0000
   8.500   1.4495   0.02632   0.01734  -0.1005   0.3717   1.0000
   8.750   1.4690   0.02693   0.01802  -0.0992   0.3604   1.0000
   9.000   1.4875   0.02767   0.01888  -0.0978   0.3502   1.0000
   9.250   1.5096   0.02834   0.01954  -0.0970   0.3408   1.0000
   9.500   1.5274   0.02906   0.02040  -0.0955   0.3308   1.0000
   9.750   1.5446   0.02985   0.02131  -0.0940   0.3211   1.0000
  10.000   1.5664   0.03056   0.02197  -0.0932   0.3112   1.0000
  10.250   1.5789   0.03137   0.02298  -0.0910   0.3008   1.0000
  10.500   1.5925   0.03222   0.02398  -0.0889   0.2901   1.0000
  10.750   1.6077   0.03303   0.02480  -0.0871   0.2787   1.0000
  11.000   1.6213   0.03383   0.02557  -0.0852   0.2660   1.0000
  11.250   1.6225   0.03473   0.02665  -0.0813   0.2534   1.0000
  11.500   1.6200   0.03570   0.02775  -0.0770   0.2408   1.0000
  11.750   1.6155   0.03678   0.02890  -0.0726   0.2282   1.0000
  12.000   1.6102   0.03800   0.03018  -0.0685   0.2158   1.0000
  12.250   1.6043   0.03939   0.03159  -0.0647   0.2036   1.0000
  12.500   1.5958   0.04110   0.03339  -0.0612   0.1919   1.0000
  12.750   1.5866   0.04319   0.03566  -0.0581   0.1801   1.0000
  13.000   1.5792   0.04547   0.03805  -0.0557   0.1690   1.0000
  13.250   1.5721   0.04793   0.04057  -0.0536   0.1589   1.0000
  13.500   1.5647   0.05060   0.04324  -0.0520   0.1494   1.0000
  13.750   1.5562   0.05375   0.04653  -0.0507   0.1395   1.0000
  14.000   1.5473   0.05709   0.04992  -0.0497   0.1304   1.0000
  14.250   1.5377   0.06061   0.05338  -0.0488   0.1221   1.0000
  14.500   1.5267   0.06457   0.05746  -0.0483   0.1136   1.0000
  14.750   1.5154   0.06873   0.06165  -0.0479   0.1052   1.0000
  15.000   1.5051   0.07279   0.06562  -0.0474   0.0969   1.0000
  15.250   1.4931   0.07734   0.07026  -0.0475   0.0893   1.0000
  15.500   1.4835   0.08165   0.07461  -0.0473   0.0821   1.0000
  15.750   1.4839   0.08440   0.07715  -0.0461   0.0745   1.0000
  16.000   1.4725   0.08940   0.08245  -0.0468   0.0708   1.0000
  16.250   1.4712   0.09268   0.08572  -0.0466   0.0663   1.0000
  16.500   1.4716   0.09587   0.08896  -0.0461   0.0625   1.0000
  16.750   1.4610   0.10094   0.09430  -0.0474   0.0603   1.0000
  17.000   1.4555   0.10522   0.09874  -0.0484   0.0579   1.0000
  17.250   1.4755   0.10543   0.09872  -0.0458   0.0543   1.0000
  17.500   1.4606   0.11132   0.10493  -0.0480   0.0536   1.0000
  17.750   1.4449   0.11762   0.11153  -0.0507   0.0530   1.0000
  18.000   1.4274   0.12450   0.11869  -0.0540   0.0526   1.0000
  18.250   1.4076   0.13213   0.12659  -0.0581   0.0523   1.0000
  18.500   1.3848   0.14079   0.13551  -0.0633   0.0523   1.0000
  18.750   1.3578   0.15091   0.14588  -0.0699   0.0527   1.0000
  19.000   1.3272   0.16271   0.15787  -0.0779   0.0534   1.0000
  19.250   1.2940   0.17623   0.17154  -0.0871   0.0541   1.0000
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