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GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il)
Reynolds number: 500,000
Max Cl/Cd: 105.72 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe300-il-500000-n5.txt
Download as CSV file: xf-goe300-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1826   0.08761   0.08515  -0.0472   0.8782   0.0100
  -8.000  -0.1768   0.08419   0.08169  -0.0491   0.8653   0.0101
  -7.750  -0.1734   0.07985   0.07731  -0.0522   0.8524   0.0105
  -7.500  -0.1641   0.07491   0.07234  -0.0573   0.8404   0.0109
  -7.250  -0.1491   0.07176   0.06914  -0.0609   0.8286   0.0111
  -7.000  -0.1322   0.06860   0.06591  -0.0648   0.8162   0.0113
  -6.750  -0.1135   0.06510   0.06234  -0.0692   0.8029   0.0115
  -6.500  -0.0929   0.06096   0.05812  -0.0745   0.7890   0.0119
  -6.000  -0.0276   0.02850   0.02449  -0.1095   0.7694   0.0168
  -5.750  -0.0011   0.02786   0.02377  -0.1098   0.7540   0.0177
  -5.500   0.0265   0.02224   0.01760  -0.1126   0.7409   0.0196
  -5.250   0.0516   0.01583   0.01039  -0.1145   0.7284   0.0222
  -5.000   0.0770   0.01315   0.00726  -0.1148   0.7144   0.0248
  -4.750   0.1041   0.01252   0.00647  -0.1147   0.7003   0.0277
  -4.500   0.1314   0.01210   0.00590  -0.1145   0.6868   0.0313
  -4.250   0.1592   0.01221   0.00598  -0.1143   0.6729   0.0343
  -4.000   0.1870   0.01227   0.00596  -0.1141   0.6596   0.0373
  -3.750   0.2145   0.01193   0.00541  -0.1139   0.6477   0.0401
  -3.500   0.2423   0.01218   0.00564  -0.1137   0.6353   0.0419
  -3.250   0.2702   0.01250   0.00593  -0.1135   0.6219   0.0436
  -3.000   0.2980   0.01257   0.00593  -0.1133   0.6098   0.0456
  -2.750   0.3256   0.01240   0.00560  -0.1132   0.5995   0.0480
  -2.500   0.3534   0.01228   0.00534  -0.1130   0.5904   0.0496
  -2.250   0.3810   0.01194   0.00488  -0.1129   0.5829   0.0511
  -2.000   0.4089   0.01188   0.00478  -0.1128   0.5751   0.0526
  -1.750   0.4366   0.01181   0.00465  -0.1127   0.5679   0.0537
  -1.500   0.4644   0.01172   0.00449  -0.1126   0.5600   0.0551
  -1.250   0.4920   0.01154   0.00421  -0.1125   0.5527   0.0563
  -1.000   0.5198   0.01131   0.00391  -0.1124   0.5455   0.0574
  -0.750   0.5473   0.01114   0.00364  -0.1122   0.5386   0.0585
  -0.500   0.5751   0.01102   0.00346  -0.1121   0.5324   0.0597
  -0.250   0.6027   0.01095   0.00333  -0.1120   0.5246   0.0606
   0.000   0.6301   0.01087   0.00319  -0.1118   0.5167   0.0610
   0.250   0.6573   0.01065   0.00292  -0.1117   0.5078   0.0624
   0.500   0.6848   0.01057   0.00282  -0.1115   0.5005   0.0635
   0.750   0.7122   0.01053   0.00275  -0.1114   0.4924   0.0645
   1.000   0.7396   0.01052   0.00272  -0.1113   0.4839   0.0656
   1.250   0.7668   0.01053   0.00269  -0.1111   0.4737   0.0667
   1.500   0.7941   0.01054   0.00267  -0.1110   0.4639   0.0681
   1.750   0.8211   0.01058   0.00267  -0.1108   0.4534   0.0697
   2.000   0.8480   0.01066   0.00270  -0.1106   0.4399   0.0717
   2.250   0.8746   0.01075   0.00274  -0.1104   0.4248   0.0734
   2.500   0.9013   0.01082   0.00278  -0.1102   0.4106   0.0767
   2.750   0.9278   0.01094   0.00287  -0.1100   0.3971   0.0800
   3.000   0.9541   0.01109   0.00297  -0.1097   0.3844   0.0837
   3.250   0.9802   0.01126   0.00309  -0.1095   0.3723   0.0875
   3.750   1.0324   0.01159   0.00339  -0.1090   0.3522   0.0998
   4.000   1.0585   0.01175   0.00355  -0.1087   0.3449   0.1078
   4.500   1.1110   0.01204   0.00389  -0.1083   0.3336   0.1302
   4.750   1.1367   0.01222   0.00410  -0.1081   0.3276   0.1550
   5.250   1.1859   0.01127   0.00461  -0.1073   0.3171   1.0000
   5.500   1.2110   0.01153   0.00483  -0.1069   0.3113   1.0000
   5.750   1.2368   0.01173   0.00503  -0.1066   0.3062   1.0000
   6.000   1.2623   0.01194   0.00525  -0.1063   0.3004   1.0000
   6.250   1.2871   0.01221   0.00549  -0.1059   0.2951   1.0000
   6.500   1.3124   0.01242   0.00573  -0.1056   0.2889   1.0000
   6.750   1.3369   0.01269   0.00598  -0.1052   0.2806   1.0000
   7.000   1.3614   0.01296   0.00625  -0.1048   0.2720   1.0000
   7.250   1.3850   0.01328   0.00655  -0.1042   0.2608   1.0000
   7.500   1.4081   0.01363   0.00686  -0.1036   0.2451   1.0000
   7.750   1.4285   0.01419   0.00728  -0.1027   0.2165   1.0000
   8.000   1.4459   0.01497   0.00787  -0.1013   0.1872   1.0000
   8.250   1.4650   0.01557   0.00842  -0.1002   0.1754   1.0000
   8.500   1.4856   0.01603   0.00889  -0.0992   0.1696   1.0000
   8.750   1.5037   0.01665   0.00948  -0.0979   0.1618   1.0000
   9.000   1.5229   0.01715   0.01001  -0.0968   0.1548   1.0000
   9.250   1.5396   0.01777   0.01062  -0.0953   0.1476   1.0000
   9.500   1.5564   0.01827   0.01115  -0.0937   0.1428   1.0000
   9.750   1.5738   0.01873   0.01166  -0.0923   0.1380   1.0000
  10.000   1.5881   0.01939   0.01232  -0.0905   0.1312   1.0000
  10.250   1.6037   0.01997   0.01295  -0.0890   0.1260   1.0000
  10.500   1.6184   0.02063   0.01362  -0.0874   0.1185   1.0000
  10.750   1.6310   0.02143   0.01442  -0.0856   0.1104   1.0000
  11.000   1.6413   0.02241   0.01537  -0.0837   0.0990   1.0000
  11.250   1.6481   0.02367   0.01657  -0.0815   0.0852   1.0000
  11.500   1.6504   0.02532   0.01814  -0.0791   0.0695   1.0000
  11.750   1.6411   0.02797   0.02063  -0.0760   0.0415   1.0000
  12.000   1.6322   0.03080   0.02339  -0.0733   0.0256   1.0000
  12.250   1.6332   0.03294   0.02559  -0.0717   0.0208   1.0000
  12.500   1.6346   0.03514   0.02785  -0.0703   0.0179   1.0000
  12.750   1.6372   0.03733   0.03012  -0.0692   0.0160   1.0000
  13.000   1.6382   0.03974   0.03261  -0.0681   0.0145   1.0000
  13.250   1.6405   0.04210   0.03507  -0.0673   0.0135   1.0000
  13.500   1.6408   0.04476   0.03783  -0.0666   0.0126   1.0000
  13.750   1.6386   0.04773   0.04089  -0.0660   0.0118   1.0000
  14.000   1.6387   0.05055   0.04382  -0.0656   0.0112   1.0000
  14.250   1.6373   0.05363   0.04701  -0.0653   0.0106   1.0000
  14.500   1.6343   0.05698   0.05045  -0.0652   0.0101   1.0000
  14.750   1.6294   0.06063   0.05420  -0.0651   0.0097   1.0000
  15.000   1.6237   0.06450   0.05817  -0.0653   0.0093   1.0000
  15.250   1.6193   0.06825   0.06205  -0.0655   0.0090   1.0000
  15.500   1.6137   0.07224   0.06615  -0.0659   0.0087   1.0000
  15.750   1.6069   0.07644   0.07047  -0.0663   0.0084   1.0000
  16.000   1.5990   0.08089   0.07503  -0.0670   0.0082   1.0000
  16.250   1.5903   0.08554   0.07979  -0.0678   0.0079   1.0000
  16.500   1.5803   0.09043   0.08479  -0.0687   0.0078   1.0000
  16.750   1.5694   0.09556   0.09005  -0.0698   0.0076   1.0000
  17.000   1.5574   0.10096   0.09556  -0.0712   0.0075   1.0000
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