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GOE 550 AIRFOIL (goe550-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 550 AIRFOIL (goe550-il)
Reynolds number: 100,000
Max Cl/Cd: 53.14 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe550-il-100000.txt
Download as CSV file: xf-goe550-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 550 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3230   0.10317   0.09798  -0.0358   1.0000   0.1737
  -8.750  -0.3695   0.10328   0.09830  -0.0358   1.0000   0.1755
  -8.500  -0.3683   0.09969   0.09476  -0.0339   1.0000   0.1767
  -8.250  -0.3464   0.09644   0.09149  -0.0312   1.0000   0.1789
  -8.000  -0.3462   0.09485   0.08995  -0.0283   1.0000   0.1820
  -7.750  -0.3601   0.09381   0.08900  -0.0253   1.0000   0.1851
  -7.500  -0.4969   0.08543   0.08091  -0.0300   1.0000   0.1466
  -7.250  -0.4940   0.08382   0.07935  -0.0262   1.0000   0.1480
  -7.000  -0.4912   0.08177   0.07730  -0.0230   1.0000   0.1431
  -6.750  -0.5346   0.04793   0.04271  -0.0586   0.9924   0.1266
  -6.500  -0.5143   0.03495   0.02827  -0.0700   0.9867   0.1342
  -6.250  -0.4747   0.03588   0.02944  -0.0719   0.9799   0.1402
  -6.000  -0.4412   0.03268   0.02564  -0.0756   0.9733   0.1490
  -5.750  -0.4044   0.03283   0.02582  -0.0775   0.9661   0.1571
  -5.500  -0.3682   0.03199   0.02483  -0.0799   0.9591   0.1660
  -5.250  -0.3342   0.03105   0.02357  -0.0820   0.9519   0.1774
  -5.000  -0.2972   0.03128   0.02387  -0.0837   0.9445   0.1870
  -4.750  -0.2641   0.03101   0.02354  -0.0851   0.9368   0.1968
  -4.500  -0.2278   0.03028   0.02253  -0.0872   0.9296   0.2089
  -4.250  -0.1941   0.03035   0.02262  -0.0884   0.9220   0.2188
  -4.000  -0.1595   0.02996   0.02217  -0.0899   0.9145   0.2289
  -3.750  -0.1214   0.02935   0.02132  -0.0922   0.9084   0.2416
  -3.500  -0.0919   0.02921   0.02120  -0.0926   0.8994   0.2512
  -3.250  -0.0473   0.02853   0.02042  -0.0958   0.8950   0.2634
  -3.000  -0.0242   0.02808   0.01971  -0.0954   0.8845   0.2742
  -2.750   0.0195   0.02745   0.01908  -0.0981   0.8798   0.2857
  -2.500   0.0445   0.02707   0.01863  -0.0979   0.8699   0.2954
  -2.250   0.0870   0.02643   0.01784  -0.1004   0.8647   0.3089
  -2.000   0.1196   0.02604   0.01745  -0.1012   0.8569   0.3192
  -1.750   0.1568   0.02548   0.01684  -0.1028   0.8499   0.3300
  -1.500   0.2072   0.02472   0.01599  -0.1065   0.8465   0.3434
  -1.250   0.2310   0.02458   0.01586  -0.1057   0.8355   0.3524
  -1.000   0.2780   0.02380   0.01506  -0.1086   0.8307   0.3642
  -0.750   0.3069   0.02358   0.01475  -0.1085   0.8204   0.3751
  -0.500   0.3501   0.02286   0.01410  -0.1105   0.8143   0.3872
  -0.250   0.3790   0.02260   0.01386  -0.1104   0.8043   0.3968
   0.000   0.4190   0.02206   0.01327  -0.1119   0.7975   0.4083
   0.250   0.4456   0.02190   0.01318  -0.1114   0.7874   0.4174
   0.500   0.4836   0.02142   0.01269  -0.1126   0.7802   0.4295
   0.750   0.5088   0.02136   0.01268  -0.1118   0.7695   0.4402
   1.000   0.5470   0.02086   0.01222  -0.1130   0.7625   0.4551
   1.250   0.5695   0.02087   0.01232  -0.1118   0.7510   0.4703
   1.500   0.6082   0.02033   0.01181  -0.1129   0.7444   0.4940
   1.750   0.6297   0.02028   0.01196  -0.1116   0.7321   0.5188
   2.000   0.6593   0.01985   0.01182  -0.1114   0.7228   0.5721
   2.250   0.7062   0.01860   0.01149  -0.1139   0.7132   1.0000
   2.500   0.7309   0.01884   0.01158  -0.1130   0.7017   1.0000
   2.750   0.7666   0.01871   0.01125  -0.1137   0.6934   1.0000
   3.000   0.7882   0.01897   0.01147  -0.1123   0.6806   1.0000
   3.250   0.8128   0.01918   0.01163  -0.1114   0.6691   1.0000
   3.500   0.8467   0.01911   0.01142  -0.1118   0.6602   1.0000
   3.750   0.8683   0.01940   0.01170  -0.1104   0.6472   1.0000
   4.000   0.8923   0.01964   0.01192  -0.1094   0.6349   1.0000
   4.250   0.9211   0.01975   0.01195  -0.1091   0.6243   1.0000
   4.500   0.9477   0.01994   0.01210  -0.1085   0.6128   1.0000
   4.750   0.9702   0.02030   0.01248  -0.1073   0.6004   1.0000
   5.000   0.9963   0.02057   0.01271  -0.1067   0.5892   1.0000
   5.250   1.0258   0.02073   0.01279  -0.1065   0.5787   1.0000
   5.500   1.0465   0.02115   0.01327  -0.1051   0.5659   1.0000
   5.750   1.0704   0.02149   0.01360  -0.1041   0.5541   1.0000
   6.000   1.0990   0.02167   0.01370  -0.1038   0.5431   1.0000
   6.250   1.1212   0.02202   0.01409  -0.1026   0.5311   1.0000
   6.500   1.1426   0.02250   0.01463  -0.1013   0.5199   1.0000
   6.750   1.1705   0.02278   0.01484  -0.1010   0.5100   1.0000
   7.000   1.1913   0.02318   0.01532  -0.0996   0.4985   1.0000
   7.250   1.2120   0.02361   0.01582  -0.0982   0.4872   1.0000
   7.500   1.2386   0.02386   0.01602  -0.0976   0.4768   1.0000
   7.750   1.2580   0.02432   0.01660  -0.0961   0.4661   1.0000
   8.000   1.2785   0.02478   0.01715  -0.0947   0.4557   1.0000
   8.250   1.3027   0.02494   0.01728  -0.0937   0.4438   1.0000
   8.500   1.3242   0.02502   0.01733  -0.0922   0.4299   1.0000
   8.750   1.3391   0.02522   0.01762  -0.0897   0.4150   1.0000
   9.000   1.3534   0.02547   0.01794  -0.0871   0.4003   1.0000
   9.250   1.3670   0.02576   0.01828  -0.0845   0.3852   1.0000
   9.500   1.3790   0.02607   0.01864  -0.0817   0.3695   1.0000
   9.750   1.3883   0.02643   0.01904  -0.0785   0.3528   1.0000
  10.000   1.3945   0.02687   0.01949  -0.0748   0.3351   1.0000
  10.250   1.3958   0.02740   0.01999  -0.0705   0.3168   1.0000
  10.500   1.3903   0.02816   0.02084  -0.0654   0.2971   1.0000
  10.750   1.3834   0.02913   0.02185  -0.0605   0.2745   1.0000
  11.000   1.3751   0.03043   0.02310  -0.0561   0.2497   1.0000
  11.250   1.3646   0.03215   0.02470  -0.0520   0.2239   1.0000
  11.500   1.3540   0.03431   0.02673  -0.0485   0.1982   1.0000
  11.750   1.3428   0.03685   0.02907  -0.0455   0.1775   1.0000
  12.000   1.3328   0.03964   0.03173  -0.0430   0.1592   1.0000
  12.250   1.3242   0.04255   0.03451  -0.0409   0.1442   1.0000
  12.500   1.3187   0.04542   0.03724  -0.0391   0.1311   1.0000
  12.750   1.3175   0.04810   0.03980  -0.0375   0.1194   1.0000
  13.000   1.3219   0.05047   0.04200  -0.0361   0.1086   1.0000
  13.250   1.3242   0.05293   0.04454  -0.0349   0.1004   1.0000
  13.500   1.3320   0.05518   0.04679  -0.0338   0.0929   1.0000
  13.750   1.3398   0.05731   0.04890  -0.0329   0.0868   1.0000
  14.000   1.3501   0.05954   0.05121  -0.0319   0.0816   1.0000
  14.250   1.3545   0.06198   0.05375  -0.0312   0.0773   1.0000
  14.500   1.3738   0.06370   0.05534  -0.0304   0.0727   1.0000
  14.750   1.3758   0.06665   0.05857  -0.0297   0.0702   1.0000
  15.000   1.3788   0.06950   0.06160  -0.0292   0.0676   1.0000
  15.250   1.3904   0.07165   0.06372  -0.0286   0.0649   1.0000
  15.500   1.3990   0.07472   0.06690  -0.0282   0.0626   1.0000
  15.750   1.3892   0.07884   0.07134  -0.0282   0.0615   1.0000
  16.000   1.3787   0.08326   0.07605  -0.0285   0.0605   1.0000
  16.250   1.3671   0.08803   0.08110  -0.0292   0.0598   1.0000
  16.500   1.3528   0.09328   0.08662  -0.0304   0.0593   1.0000
  16.750   1.3344   0.09924   0.09285  -0.0323   0.0590   1.0000
  17.000   1.3110   0.10616   0.10006  -0.0351   0.0590   1.0000
  17.250   1.2813   0.11447   0.10867  -0.0392   0.0593   1.0000
  17.500   1.2444   0.12470   0.11919  -0.0451   0.0600   1.0000
  17.750   1.2017   0.13712   0.13186  -0.0530   0.0611   1.0000
  18.000   1.1556   0.15189   0.14681  -0.0627   0.0624   1.0000
  18.250   1.1220   0.16548   0.16047  -0.0711   0.0634   1.0000
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