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GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 176 (ALBATROS 7020) AIRFOIL (goe176-il)
Reynolds number: 100,000
Max Cl/Cd: 55.98 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe176-il-100000.txt
Download as CSV file: xf-goe176-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 176 (ALBATROS 7020) 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  -0.2954   0.09642   0.09208  -0.0278   1.0000   0.1076
  -7.250  -0.3215   0.09683   0.09271  -0.0302   1.0000   0.1091
  -7.000  -0.3232   0.09327   0.08926  -0.0287   1.0000   0.1104
  -6.750  -0.3103   0.08979   0.08578  -0.0234   1.0000   0.1132
  -6.500  -0.3158   0.08824   0.08433  -0.0209   1.0000   0.1158
  -6.250  -0.3278   0.08716   0.08336  -0.0188   1.0000   0.1184
  -5.750  -0.3528   0.08418   0.08056  -0.0250   1.0000   0.1244
  -5.250  -0.2782   0.07416   0.07046  -0.0378   0.9855   0.1398
  -5.000  -0.2316   0.06897   0.06517  -0.0497   0.9755   0.1530
  -4.750  -0.1422   0.04227   0.03726  -0.0877   0.9705   0.0819
  -4.500  -0.0852   0.03196   0.02562  -0.0986   0.9654   0.0692
  -4.250  -0.0326   0.02754   0.02048  -0.1045   0.9606   0.0685
  -4.000   0.0111   0.02481   0.01738  -0.1081   0.9515   0.0726
  -3.750   0.0585   0.02283   0.01507  -0.1117   0.9441   0.0768
  -3.500   0.1054   0.02112   0.01313  -0.1149   0.9358   0.0843
  -3.250   0.1501   0.01978   0.01175  -0.1177   0.9262   0.0976
  -3.000   0.2008   0.01835   0.01054  -0.1217   0.9202   0.1393
  -2.750   0.2414   0.01918   0.01155  -0.1232   0.9084   0.2500
  -2.500   0.2806   0.01944   0.01168  -0.1248   0.8973   0.2873
  -2.250   0.3212   0.01928   0.01149  -0.1267   0.8872   0.3170
  -2.000   0.3578   0.01898   0.01120  -0.1278   0.8751   0.3410
  -1.750   0.3918   0.01852   0.01060  -0.1284   0.8610   0.3542
  -1.500   0.4245   0.01811   0.01004  -0.1288   0.8462   0.3657
  -1.250   0.4556   0.01781   0.00956  -0.1289   0.8309   0.3771
  -1.000   0.4846   0.01756   0.00924  -0.1286   0.8162   0.3885
  -0.750   0.5128   0.01736   0.00898  -0.1282   0.8020   0.4005
  -0.500   0.5405   0.01720   0.00875  -0.1278   0.7877   0.4128
  -0.250   0.5681   0.01705   0.00854  -0.1273   0.7734   0.4262
   0.000   0.5952   0.01690   0.00835  -0.1267   0.7589   0.4403
   0.250   0.6218   0.01674   0.00817  -0.1259   0.7440   0.4559
   0.500   0.6483   0.01656   0.00799  -0.1251   0.7285   0.4757
   0.750   0.6748   0.01635   0.00779  -0.1243   0.7123   0.5016
   1.000   0.7008   0.01600   0.00758  -0.1234   0.6955   0.5458
   1.250   0.7222   0.01491   0.00731  -0.1210   0.6785   1.0000
   1.500   0.7494   0.01508   0.00717  -0.1204   0.6591   1.0000
   1.750   0.7752   0.01527   0.00715  -0.1195   0.6371   1.0000
   2.000   0.8015   0.01550   0.00712  -0.1187   0.6156   1.0000
   2.250   0.8265   0.01582   0.00727  -0.1178   0.5912   1.0000
   2.500   0.8527   0.01620   0.00738  -0.1171   0.5708   1.0000
   2.750   0.8779   0.01664   0.00768  -0.1164   0.5503   1.0000
   3.000   0.9038   0.01708   0.00801  -0.1159   0.5338   1.0000
   3.250   0.9299   0.01753   0.00833  -0.1155   0.5200   1.0000
   3.500   0.9561   0.01795   0.00862  -0.1150   0.5076   1.0000
   3.750   0.9820   0.01832   0.00888  -0.1145   0.4955   1.0000
   4.000   1.0069   0.01866   0.00923  -0.1139   0.4828   1.0000
   4.250   1.0318   0.01899   0.00954  -0.1133   0.4711   1.0000
   4.500   1.0571   0.01932   0.00982  -0.1128   0.4607   1.0000
   4.750   1.0825   0.01964   0.01008  -0.1122   0.4510   1.0000
   5.000   1.1071   0.02000   0.01053  -0.1116   0.4413   1.0000
   5.250   1.1324   0.02034   0.01083  -0.1111   0.4327   1.0000
   5.500   1.1572   0.02072   0.01126  -0.1106   0.4242   1.0000
   5.750   1.1826   0.02115   0.01174  -0.1101   0.4175   1.0000
   6.000   1.2073   0.02157   0.01221  -0.1096   0.4097   1.0000
   6.250   1.2321   0.02201   0.01269  -0.1091   0.4024   1.0000
   6.500   1.2567   0.02246   0.01322  -0.1085   0.3952   1.0000
   6.750   1.2817   0.02298   0.01380  -0.1081   0.3889   1.0000
   7.000   1.3055   0.02349   0.01443  -0.1074   0.3816   1.0000
   7.250   1.3304   0.02403   0.01500  -0.1069   0.3747   1.0000
   7.500   1.3532   0.02459   0.01570  -0.1062   0.3667   1.0000
   7.750   1.3774   0.02519   0.01638  -0.1056   0.3593   1.0000
   8.000   1.3998   0.02576   0.01707  -0.1047   0.3505   1.0000
   8.250   1.4205   0.02634   0.01778  -0.1036   0.3401   1.0000
   8.500   1.4400   0.02682   0.01830  -0.1023   0.3268   1.0000
   8.750   1.4581   0.02727   0.01882  -0.1008   0.3130   1.0000
   9.000   1.4776   0.02774   0.01932  -0.0995   0.3013   1.0000
   9.250   1.4927   0.02823   0.02013  -0.0975   0.2904   1.0000
   9.500   1.5080   0.02867   0.02080  -0.0956   0.2790   1.0000
   9.750   1.5200   0.02899   0.02134  -0.0932   0.2646   1.0000
  10.000   1.5318   0.02938   0.02200  -0.0907   0.2495   1.0000
  10.250   1.5437   0.02986   0.02274  -0.0884   0.2333   1.0000
  10.500   1.5528   0.03045   0.02351  -0.0857   0.2110   1.0000
  10.750   1.5500   0.03151   0.02440  -0.0816   0.1799   1.0000
  11.000   1.5397   0.03356   0.02620  -0.0774   0.1536   1.0000
  11.250   1.5286   0.03618   0.02872  -0.0738   0.1320   1.0000
  11.750   1.5022   0.04291   0.03537  -0.0687   0.0793   1.0000
  12.000   1.4828   0.04741   0.03976  -0.0674   0.0703   1.0000
  12.250   1.4626   0.05246   0.04484  -0.0669   0.0661   1.0000
  12.500   1.4410   0.05809   0.05052  -0.0672   0.0633   1.0000
  12.750   1.4222   0.06372   0.05633  -0.0678   0.0607   1.0000
  13.000   1.4034   0.06953   0.06229  -0.0687   0.0585   1.0000
  13.250   1.3854   0.07528   0.06815  -0.0696   0.0566   1.0000
  13.500   1.3699   0.08042   0.07331  -0.0699   0.0544   1.0000
  13.750   1.3654   0.08365   0.07656  -0.0688   0.0511   1.0000
  14.000   1.3648   0.08666   0.07965  -0.0680   0.0479   1.0000
  14.250   1.3691   0.08850   0.08144  -0.0661   0.0445   1.0000
  14.500   1.3786   0.08981   0.08272  -0.0636   0.0415   1.0000
  14.750   1.3817   0.09278   0.08588  -0.0633   0.0398   1.0000
  15.000   1.3881   0.09520   0.08845  -0.0623   0.0383   1.0000
  15.250   1.3933   0.09790   0.09130  -0.0615   0.0372   1.0000
  15.500   1.3976   0.10083   0.09435  -0.0610   0.0362   1.0000
  15.750   1.4019   0.10386   0.09751  -0.0605   0.0354   1.0000
  16.000   1.4075   0.10682   0.10057  -0.0598   0.0347   1.0000
  16.250   1.4171   0.10981   0.10359  -0.0583   0.0338   1.0000
  16.500   1.4038   0.11553   0.10957  -0.0609   0.0337   1.0000
  16.750   1.3909   0.12150   0.11579  -0.0638   0.0336   1.0000
  17.000   1.3768   0.12793   0.12245  -0.0673   0.0336   1.0000
  17.250   1.3618   0.13480   0.12954  -0.0715   0.0336   1.0000
  17.500   1.3463   0.14211   0.13706  -0.0761   0.0337   1.0000
  17.750   1.3315   0.14966   0.14480  -0.0809   0.0338   1.0000
  18.000   0.8975   0.17232   0.16847  -0.0806   0.0517   1.0000
  18.250   0.8794   0.18084   0.17696  -0.0840   0.0526   1.0000
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