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GOE 490 AIRFOIL (goe490-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 490 AIRFOIL (goe490-il)
Reynolds number: 50,000
Max Cl/Cd: 33.18 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe490-il-50000.txt
Download as CSV file: xf-goe490-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 490 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3584   0.11741   0.11024  -0.0226   1.0000   0.1703
  -9.250  -0.3662   0.11629   0.10923  -0.0237   1.0000   0.1753
  -9.000  -0.3739   0.11444   0.10750  -0.0246   1.0000   0.1775
  -8.750  -0.3531   0.10892   0.10195  -0.0228   1.0000   0.1843
  -8.500  -0.3625   0.10778   0.10093  -0.0234   1.0000   0.1900
  -8.250  -0.3587   0.10412   0.09734  -0.0229   1.0000   0.1944
  -8.000  -0.3573   0.10165   0.09493  -0.0221   1.0000   0.2033
  -7.750  -0.3815   0.10181   0.09529  -0.0220   1.0000   0.2058
  -7.500  -0.3588   0.09638   0.08984  -0.0203   1.0000   0.2168
  -7.250  -0.3856   0.09647   0.09014  -0.0197   1.0000   0.2203
  -7.000  -0.3672   0.09154   0.08518  -0.0174   1.0000   0.2290
  -6.750  -0.3904   0.09120   0.08505  -0.0178   1.0000   0.2351
  -6.500  -0.3776   0.08677   0.08063  -0.0150   1.0000   0.2420
  -6.250  -0.3968   0.08617   0.08016  -0.0160   1.0000   0.2502
  -6.000  -0.3855   0.08191   0.07595  -0.0125   1.0000   0.2576
  -5.750  -0.3999   0.08056   0.07469  -0.0134   1.0000   0.2664
  -5.500  -0.3993   0.07795   0.07214  -0.0113   1.0000   0.2790
  -5.250  -0.3977   0.07501   0.06926  -0.0087   1.0000   0.2922
  -5.000  -0.3988   0.07245   0.06675  -0.0069   1.0000   0.3063
  -4.750  -0.4031   0.07030   0.06464  -0.0065   1.0000   0.3238
  -4.500  -0.4005   0.06724   0.06164  -0.0033   1.0000   0.3399
  -4.250  -0.3980   0.06449   0.05895  -0.0002   1.0000   0.3579
  -4.000  -0.3988   0.06209   0.05659   0.0024   1.0000   0.3852
  -3.750  -0.3989   0.05968   0.05423   0.0065   1.0000   0.4160
  -3.000  -0.2711   0.04373   0.03617  -0.0270   1.0000   0.1938
  -2.750  -0.2429   0.03992   0.03165  -0.0285   1.0000   0.1753
  -2.500  -0.2215   0.03752   0.02895  -0.0283   1.0000   0.1734
  -2.250  -0.1982   0.03548   0.02631  -0.0282   1.0000   0.1765
  -2.000  -0.1790   0.03390   0.02464  -0.0275   1.0000   0.1807
  -1.750  -0.1575   0.03238   0.02277  -0.0269   1.0000   0.1842
  -1.500  -0.1350   0.03101   0.02093  -0.0263   1.0000   0.1901
  -1.250  -0.1156   0.03025   0.02005  -0.0255   1.0000   0.2038
  -1.000  -0.0948   0.02955   0.01918  -0.0249   1.0000   0.2220
  -0.750  -0.0758   0.02892   0.01852  -0.0240   1.0000   0.2447
  -0.500  -0.0576   0.02852   0.01798  -0.0230   1.0000   0.2810
  -0.250  -0.0344   0.02805   0.01751  -0.0232   1.0000   0.3276
   0.000   0.0102   0.02766   0.01722  -0.0273   0.9932   0.3895
   0.250   0.0676   0.02719   0.01727  -0.0336   0.9785   0.4787
   0.500   0.1472   0.02641   0.01733  -0.0437   0.9625   1.0000
   0.750   0.2038   0.02745   0.01787  -0.0498   0.9445   1.0000
   1.000   0.2483   0.02819   0.01834  -0.0537   0.9244   1.0000
   1.250   0.2962   0.02887   0.01882  -0.0580   0.9051   1.0000
   1.500   0.3473   0.02945   0.01923  -0.0626   0.8869   1.0000
   1.750   0.3850   0.02996   0.01964  -0.0647   0.8665   1.0000
   2.000   0.4268   0.03036   0.01997  -0.0673   0.8474   1.0000
   2.250   0.4747   0.03054   0.02009  -0.0704   0.8295   1.0000
   2.500   0.5278   0.03039   0.01993  -0.0740   0.8126   1.0000
   2.750   0.5602   0.03061   0.02016  -0.0744   0.7923   1.0000
   3.000   0.6038   0.03043   0.01999  -0.0761   0.7741   1.0000
   3.250   0.6490   0.03003   0.01963  -0.0777   0.7567   1.0000
   3.500   0.6945   0.02951   0.01917  -0.0790   0.7398   1.0000
   3.750   0.7283   0.02940   0.01910  -0.0787   0.7212   1.0000
   4.000   0.7563   0.02952   0.01929  -0.0778   0.7014   1.0000
   4.250   0.7931   0.02919   0.01901  -0.0776   0.6826   1.0000
   4.500   0.8316   0.02875   0.01859  -0.0775   0.6637   1.0000
   4.750   0.8520   0.02917   0.01906  -0.0755   0.6413   1.0000
   5.000   0.8890   0.02872   0.01864  -0.0750   0.6202   1.0000
   5.250   0.9086   0.02918   0.01915  -0.0727   0.5966   1.0000
   5.500   0.9400   0.02905   0.01899  -0.0717   0.5739   1.0000
   5.750   0.9606   0.02955   0.01956  -0.0696   0.5502   1.0000
   6.000   0.9859   0.02993   0.01993  -0.0681   0.5279   1.0000
   6.250   1.0078   0.03056   0.02059  -0.0664   0.5057   1.0000
   6.500   1.0334   0.03115   0.02116  -0.0652   0.4854   1.0000
   6.750   1.0504   0.03227   0.02242  -0.0632   0.4656   1.0000
   7.000   1.0717   0.03327   0.02348  -0.0617   0.4473   1.0000
   7.250   1.0925   0.03444   0.02473  -0.0603   0.4310   1.0000
   7.500   1.1099   0.03595   0.02640  -0.0587   0.4168   1.0000
   7.750   1.1245   0.03771   0.02837  -0.0568   0.4042   1.0000
   8.000   1.1402   0.03944   0.03032  -0.0552   0.3927   1.0000
   8.250   1.1587   0.04068   0.03170  -0.0536   0.3796   1.0000
   8.500   1.1750   0.04155   0.03270  -0.0515   0.3640   1.0000
   8.750   1.1936   0.04152   0.03275  -0.0493   0.3447   1.0000
   9.000   1.2111   0.04208   0.03345  -0.0473   0.3299   1.0000
   9.250   1.2414   0.04084   0.03214  -0.0460   0.3094   1.0000
   9.500   1.2472   0.04081   0.03232  -0.0423   0.2895   1.0000
   9.750   1.2538   0.03918   0.03057  -0.0381   0.2613   1.0000
  10.000   1.2534   0.03866   0.02998  -0.0334   0.2360   1.0000
  10.250   1.2437   0.03920   0.03061  -0.0281   0.2115   1.0000
  10.500   1.2264   0.04041   0.03184  -0.0222   0.1858   1.0000
  10.750   1.2080   0.04237   0.03368  -0.0170   0.1594   1.0000
  11.000   1.1923   0.04503   0.03609  -0.0131   0.1359   1.0000
  11.250   1.1848   0.04794   0.03890  -0.0103   0.1189   1.0000
  11.500   1.1834   0.05078   0.04171  -0.0083   0.1073   1.0000
  11.750   1.1852   0.05339   0.04420  -0.0066   0.0987   1.0000
  12.000   1.1863   0.05641   0.04752  -0.0052   0.0922   1.0000
  12.250   1.1905   0.05902   0.05005  -0.0040   0.0865   1.0000
  12.500   1.1895   0.06260   0.05397  -0.0030   0.0829   1.0000
  12.750   1.1909   0.06607   0.05764  -0.0021   0.0799   1.0000
  13.000   1.1942   0.06948   0.06119  -0.0015   0.0780   1.0000
  13.250   1.2021   0.07310   0.06485  -0.0007   0.0761   1.0000
  13.500   1.1872   0.07823   0.07030  -0.0011   0.0759   1.0000
  13.750   1.1689   0.08393   0.07626  -0.0024   0.0759   1.0000
  14.000   1.1494   0.09008   0.08264  -0.0044   0.0762   1.0000
  14.250   0.9830   0.12727   0.12038  -0.0306   0.0966   1.0000
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