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GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 505 AIRFOIL (goe505-il)
Reynolds number: 100,000
Max Cl/Cd: 49.13 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe505-il-100000.txt
Download as CSV file: xf-goe505-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 505 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3801   0.11393   0.10998  -0.0189   0.9931   0.1195
  -7.000  -0.4122   0.11296   0.10907  -0.0221   0.9865   0.1218
  -6.750  -0.4295   0.10950   0.10560  -0.0290   0.9792   0.1232
  -6.500  -0.3874   0.10483   0.10095  -0.0257   0.9743   0.1261
  -6.250  -0.3695   0.10175   0.09783  -0.0280   0.9681   0.1296
  -6.000  -0.3708   0.09892   0.09499  -0.0300   0.9602   0.1338
  -5.750  -0.3825   0.09510   0.09104  -0.0385   0.9510   0.1385
  -5.500  -0.3625   0.09145   0.08744  -0.0368   0.9446   0.1402
  -5.250  -0.3420   0.08858   0.08455  -0.0375   0.9376   0.1440
  -5.000  -0.3366   0.08516   0.08084  -0.0453   0.9277   0.1537
  -4.750  -0.3211   0.08179   0.07758  -0.0431   0.9202   0.1557
  -4.500  -0.2983   0.07907   0.07483  -0.0436   0.9125   0.1608
  -4.250  -0.2840   0.07561   0.07109  -0.0483   0.9012   0.1702
  -4.000  -0.2660   0.05881   0.05302  -0.0556   0.8973   0.1082
  -3.750  -0.2415   0.05727   0.05171  -0.0556   0.8854   0.1107
  -3.500  -0.2021   0.05014   0.04389  -0.0591   0.8795   0.1003
  -3.250  -0.1927   0.04465   0.03749  -0.0565   0.8685   0.0971
  -3.000  -0.1624   0.04155   0.03371  -0.0565   0.8591   0.0966
  -2.750  -0.1238   0.03962   0.03143  -0.0579   0.8508   0.0985
  -2.500  -0.0999   0.03846   0.03002  -0.0570   0.8408   0.1005
  -2.250  -0.0587   0.03715   0.02835  -0.0587   0.8347   0.1060
  -2.000  -0.0356   0.03630   0.02738  -0.0576   0.8245   0.1113
  -1.750   0.0084   0.03524   0.02613  -0.0596   0.8186   0.1219
  -1.500   0.0305   0.03469   0.02567  -0.0584   0.8080   0.1335
  -1.250   0.0737   0.03398   0.02494  -0.0602   0.8022   0.1692
  -1.000   0.0933   0.03397   0.02507  -0.0585   0.7906   0.1943
  -0.750   0.1375   0.03337   0.02446  -0.0606   0.7855   0.2241
  -0.500   0.1563   0.03334   0.02446  -0.0588   0.7733   0.2450
  -0.250   0.2027   0.03251   0.02365  -0.0610   0.7689   0.2756
   0.000   0.2234   0.03218   0.02332  -0.0594   0.7564   0.2931
   0.250   0.2732   0.03095   0.02203  -0.0620   0.7527   0.3196
   0.500   0.2946   0.03053   0.02162  -0.0605   0.7401   0.3366
   0.750   0.3466   0.02900   0.02016  -0.0635   0.7369   0.3629
   1.250   0.6416   0.02322   0.01619  -0.1069   0.7374   1.0000
   1.500   0.4648   0.02544   0.01698  -0.0671   0.7094   0.4661
   1.750   0.6967   0.02193   0.01454  -0.1047   0.7098   1.0000
   2.000   0.7329   0.02108   0.01354  -0.1052   0.6947   1.0000
   2.250   0.7739   0.02021   0.01249  -0.1066   0.6770   1.0000
   2.500   0.8187   0.01945   0.01151  -0.1089   0.6554   1.0000
   2.750   0.8541   0.01906   0.01088  -0.1096   0.6292   1.0000
   3.000   0.8873   0.01898   0.01050  -0.1102   0.6029   1.0000
   3.250   0.9204   0.01909   0.01030  -0.1109   0.5793   1.0000
   3.500   0.9449   0.01943   0.01039  -0.1102   0.5586   1.0000
   3.750   0.9677   0.01982   0.01057  -0.1092   0.5413   1.0000
   4.000   0.9930   0.02024   0.01079  -0.1088   0.5268   1.0000
   4.250   1.0166   0.02069   0.01109  -0.1081   0.5142   1.0000
   4.500   1.0349   0.02118   0.01150  -0.1064   0.5028   1.0000
   4.750   1.0593   0.02167   0.01186  -0.1059   0.4927   1.0000
   5.000   1.0810   0.02213   0.01222  -0.1049   0.4828   1.0000
   5.250   1.0981   0.02264   0.01270  -0.1030   0.4734   1.0000
   5.500   1.1257   0.02312   0.01301  -0.1032   0.4645   1.0000
   5.750   1.1365   0.02364   0.01358  -0.1002   0.4560   1.0000
   6.000   1.1656   0.02415   0.01395  -0.1006   0.4483   1.0000
   6.250   1.1774   0.02473   0.01461  -0.0979   0.4413   1.0000
   6.500   1.2002   0.02527   0.01510  -0.0971   0.4345   1.0000
   6.750   1.2222   0.02590   0.01571  -0.0964   0.4283   1.0000
   7.000   1.2354   0.02650   0.01640  -0.0939   0.4220   1.0000
   7.250   1.2660   0.02710   0.01690  -0.0947   0.4161   1.0000
   7.500   1.2782   0.02783   0.01773  -0.0922   0.4106   1.0000
   7.750   1.2924   0.02849   0.01848  -0.0900   0.4047   1.0000
   8.000   1.3278   0.02915   0.01901  -0.0918   0.3988   1.0000
   8.250   1.3303   0.02993   0.01999  -0.0875   0.3934   1.0000
   8.500   1.3446   0.03061   0.02074  -0.0854   0.3875   1.0000
   8.750   1.3803   0.03133   0.02136  -0.0872   0.3817   1.0000
   9.000   1.3764   0.03218   0.02245  -0.0819   0.3763   1.0000
   9.250   1.3930   0.03270   0.02297  -0.0802   0.3693   1.0000
   9.500   1.4060   0.03333   0.02362  -0.0779   0.3621   1.0000
   9.750   1.4096   0.03389   0.02428  -0.0740   0.3550   1.0000
  10.000   1.4281   0.03422   0.02453  -0.0726   0.3468   1.0000
  10.250   1.4218   0.03494   0.02541  -0.0670   0.3411   1.0000
  10.500   1.4542   0.03504   0.02531  -0.0680   0.3326   1.0000
  10.750   1.4393   0.03601   0.02654  -0.0612   0.3281   1.0000
  11.000   1.4431   0.03664   0.02728  -0.0577   0.3222   1.0000
  11.250   1.4673   0.03690   0.02745  -0.0574   0.3154   1.0000
  11.500   1.4510   0.03792   0.02870  -0.0511   0.3098   1.0000
  11.750   1.4674   0.03794   0.02864  -0.0495   0.3026   1.0000
  12.000   1.4671   0.03892   0.02976  -0.0459   0.2976   1.0000
  12.250   1.4596   0.04010   0.03114  -0.0416   0.2926   1.0000
  12.500   1.4785   0.04006   0.03104  -0.0405   0.2861   1.0000
  12.750   1.4648   0.04144   0.03262  -0.0358   0.2805   1.0000
  13.000   1.4591   0.04260   0.03392  -0.0323   0.2749   1.0000
  13.250   1.4685   0.04278   0.03404  -0.0303   0.2681   1.0000
  13.500   1.4532   0.04486   0.03639  -0.0264   0.2633   1.0000
  13.750   1.4519   0.04588   0.03749  -0.0238   0.2570   1.0000
  14.000   1.4469   0.04736   0.03907  -0.0213   0.2512   1.0000
  14.250   1.4352   0.04965   0.04158  -0.0186   0.2456   1.0000
  14.500   1.4387   0.05070   0.04266  -0.0170   0.2399   1.0000
  14.750   1.4243   0.05366   0.04585  -0.0149   0.2346   1.0000
  15.000   1.4140   0.05634   0.04868  -0.0132   0.2282   1.0000
  15.250   1.4055   0.05906   0.05149  -0.0120   0.2219   1.0000
  15.500   1.3902   0.06297   0.05562  -0.0111   0.2165   1.0000
  15.750   1.3845   0.06581   0.05849  -0.0105   0.2096   1.0000
  16.000   1.3623   0.07118   0.06411  -0.0104   0.2049   1.0000
  16.250   1.3463   0.07589   0.06894  -0.0107   0.1985   1.0000
  16.500   1.3243   0.08178   0.07497  -0.0115   0.1931   1.0000
  16.750   1.2930   0.08939   0.08278  -0.0130   0.1903   1.0000
  17.000   1.2599   0.09765   0.09124  -0.0150   0.1898   1.0000
  17.250   1.2590   0.10081   0.09440  -0.0158   0.1809   1.0000
  17.500   1.2226   0.11002   0.10380  -0.0186   0.1801   1.0000
  17.750   1.1728   0.12201   0.11592  -0.0225   0.1803   1.0000
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