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GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 711 AIRFOIL (goe711-il)
Reynolds number: 50,000
Max Cl/Cd: 33.23 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe711-il-50000-n5.txt
Download as CSV file: xf-goe711-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 711 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3101   0.13026   0.12446  -0.0262   1.0000   0.0989
  -8.250  -0.3146   0.12834   0.12259  -0.0327   0.9930   0.1020
  -8.000  -0.3244   0.12661   0.12090  -0.0394   0.9838   0.1028
  -7.750  -0.2855   0.11906   0.11333  -0.0377   0.9824   0.1063
  -7.500  -0.2694   0.11532   0.10957  -0.0397   0.9764   0.1115
  -7.250  -0.2725   0.11285   0.10714  -0.0437   0.9669   0.1171
  -7.000  -0.2778   0.10977   0.10407  -0.0562   0.9529   0.1200
  -6.750  -0.2488   0.10489   0.09920  -0.0493   0.9518   0.1266
  -6.500  -0.2457   0.10171   0.09598  -0.0583   0.9392   0.1358
  -6.250  -0.2278   0.09687   0.09116  -0.0599   0.9333   0.1396
  -6.000  -0.2135   0.09357   0.08786  -0.0599   0.9250   0.1456
  -5.750  -0.1980   0.08920   0.08340  -0.0678   0.9164   0.1561
  -5.500  -0.1858   0.08625   0.08047  -0.0663   0.9068   0.1632
  -5.250  -0.1630   0.08229   0.07645  -0.0705   0.9007   0.1790
  -5.000  -0.1531   0.07931   0.07343  -0.0715   0.8894   0.1942
  -4.750  -0.1374   0.07619   0.07027  -0.0729   0.8800   0.2115
  -4.500  -0.1140   0.07280   0.06682  -0.0753   0.8727   0.2319
  -4.000  -0.0074   0.05753   0.04956  -0.0976   0.8569   0.0862
  -3.750   0.0136   0.05472   0.04665  -0.0979   0.8459   0.0845
  -3.500   0.0456   0.05168   0.04329  -0.0999   0.8380   0.0822
  -3.250   0.0794   0.04887   0.04008  -0.1019   0.8296   0.0802
  -3.000   0.1095   0.04671   0.03754  -0.1029   0.8197   0.0807
  -2.750   0.1498   0.04434   0.03469  -0.1053   0.8131   0.0820
  -2.500   0.1785   0.04264   0.03262  -0.1056   0.8021   0.0817
  -2.250   0.2220   0.04039   0.02995  -0.1080   0.7966   0.0813
  -2.000   0.2495   0.03909   0.02834  -0.1078   0.7848   0.0813
  -1.750   0.2953   0.03720   0.02604  -0.1102   0.7797   0.0828
  -1.500   0.3217   0.03635   0.02490  -0.1096   0.7670   0.0851
  -1.250   0.3531   0.03539   0.02365  -0.1097   0.7562   0.0866
  -1.000   0.3943   0.03387   0.02195  -0.1112   0.7489   0.0878
  -0.750   0.4218   0.03306   0.02103  -0.1107   0.7366   0.0894
  -0.500   0.4560   0.03215   0.01997  -0.1112   0.7263   0.0919
  -0.250   0.4927   0.03124   0.01890  -0.1121   0.7167   0.0976
   0.000   0.5207   0.03082   0.01829  -0.1117   0.7037   0.1027
   0.250   0.5514   0.03019   0.01759  -0.1120   0.6916   0.1079
   0.500   0.5867   0.02953   0.01676  -0.1129   0.6807   0.1160
   0.750   0.6184   0.02901   0.01618  -0.1133   0.6682   0.1332
   1.000   0.6451   0.02765   0.01605  -0.1137   0.6550   0.4163
   1.500   0.6983   0.02655   0.01539  -0.1114   0.6289   1.0000
   1.750   0.7286   0.02661   0.01511  -0.1116   0.6164   1.0000
   2.000   0.7560   0.02681   0.01502  -0.1114   0.6035   1.0000
   2.250   0.7801   0.02715   0.01515  -0.1108   0.5901   1.0000
   2.500   0.8052   0.02748   0.01527  -0.1104   0.5774   1.0000
   2.750   0.8323   0.02776   0.01533  -0.1103   0.5657   1.0000
   3.000   0.8601   0.02804   0.01539  -0.1103   0.5546   1.0000
   3.250   0.8818   0.02855   0.01578  -0.1095   0.5427   1.0000
   3.500   0.9070   0.02898   0.01605  -0.1092   0.5322   1.0000
   3.750   0.9345   0.02932   0.01623  -0.1093   0.5224   1.0000
   4.000   0.9550   0.02994   0.01678  -0.1083   0.5119   1.0000
   4.250   0.9832   0.03032   0.01700  -0.1086   0.5035   1.0000
   4.500   1.0034   0.03098   0.01763  -0.1077   0.4939   1.0000
   4.750   1.0294   0.03147   0.01801  -0.1077   0.4860   1.0000
   5.000   1.0502   0.03214   0.01867  -0.1069   0.4775   1.0000
   5.250   1.0764   0.03266   0.01909  -0.1069   0.4704   1.0000
   5.500   1.0947   0.03346   0.01992  -0.1058   0.4625   1.0000
   5.750   1.1250   0.03386   0.02020  -0.1065   0.4566   1.0000
   6.000   1.1377   0.03489   0.02134  -0.1046   0.4489   1.0000
   6.250   1.1625   0.03549   0.02189  -0.1045   0.4428   1.0000
   6.500   1.1827   0.03631   0.02275  -0.1038   0.4369   1.0000
   6.750   1.1982   0.03730   0.02382  -0.1024   0.4306   1.0000
   7.000   1.2253   0.03787   0.02435  -0.1027   0.4256   1.0000
   7.250   1.2384   0.03900   0.02559  -0.1010   0.4200   1.0000
   7.500   1.2513   0.04011   0.02681  -0.0993   0.4143   1.0000
   7.750   1.2776   0.04073   0.02742  -0.0995   0.4097   1.0000
   8.000   1.2888   0.04198   0.02878  -0.0976   0.4049   1.0000
   8.250   1.2903   0.04359   0.03058  -0.0944   0.3999   1.0000
   8.500   1.3087   0.04456   0.03161  -0.0936   0.3955   1.0000
   8.750   1.3433   0.04493   0.03195  -0.0950   0.3918   1.0000
   9.000   1.3182   0.04786   0.03518  -0.0886   0.3865   1.0000
   9.250   1.3181   0.04985   0.03731  -0.0859   0.3818   1.0000
   9.500   1.3409   0.05065   0.03820  -0.0857   0.3781   1.0000
   9.750   1.3551   0.05203   0.03967  -0.0846   0.3746   1.0000
  10.000   1.2891   0.05879   0.04677  -0.0767   0.3684   1.0000
  10.250   1.2851   0.06166   0.04977  -0.0747   0.3639   1.0000
  10.500   1.3194   0.06140   0.04955  -0.0752   0.3611   1.0000
  10.750   1.1511   0.08275   0.07121  -0.0697   0.3467   1.0000
  11.000   1.1778   0.08260   0.07115  -0.0691   0.3448   1.0000
  11.500   1.1012   0.10144   0.09018  -0.0708   0.3280   1.0000
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