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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 100,000
Max Cl/Cd: 59.48 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602m-il-100000.txt
Download as CSV file: xf-goe602m-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3671   0.09437   0.08974  -0.0321   1.0000   0.1046
  -7.750  -0.3836   0.09293   0.08841  -0.0312   1.0000   0.1071
  -7.500  -0.4096   0.09214   0.08778  -0.0298   1.0000   0.1083
  -7.250  -0.4373   0.09021   0.08598  -0.0358   1.0000   0.1093
  -7.000  -0.4245   0.08609   0.08188  -0.0281   1.0000   0.1117
  -6.750  -0.4185   0.08403   0.07984  -0.0243   1.0000   0.1165
  -6.500  -0.4282   0.08146   0.07733  -0.0257   1.0000   0.1212
  -6.250  -0.4415   0.07654   0.07239  -0.0361   1.0000   0.1248
  -6.000  -0.4332   0.07540   0.07136  -0.0257   1.0000   0.1293
  -5.500  -0.4300   0.06837   0.06433  -0.0298   1.0000   0.1422
  -5.000  -0.4101   0.06138   0.05705  -0.0378   1.0000   0.1673
  -4.750  -0.4038   0.05831   0.05410  -0.0345   1.0000   0.1704
  -4.500  -0.3910   0.05537   0.05108  -0.0356   1.0000   0.1843
  -4.250  -0.3286   0.03760   0.03158  -0.0527   1.0000   0.0982
  -4.000  -0.3011   0.03343   0.02680  -0.0537   1.0000   0.0888
  -3.750  -0.2710   0.02983   0.02206  -0.0542   1.0000   0.0820
  -3.500  -0.2492   0.02788   0.01994  -0.0539   1.0000   0.0845
  -3.250  -0.2205   0.02660   0.01841  -0.0547   0.9981   0.0887
  -3.000  -0.1768   0.02508   0.01642  -0.0575   0.9921   0.0909
  -2.750  -0.1339   0.02402   0.01504  -0.0604   0.9853   0.0970
  -2.500  -0.0937   0.02311   0.01407  -0.0629   0.9778   0.1037
  -2.250  -0.0502   0.02234   0.01323  -0.0659   0.9713   0.1118
  -2.000  -0.0138   0.02161   0.01263  -0.0678   0.9622   0.1298
  -1.750   0.0300   0.02013   0.01200  -0.0711   0.9569   0.2599
  -1.500   0.0609   0.01953   0.01214  -0.0718   0.9467   0.4743
  -1.250   0.0969   0.01941   0.01228  -0.0733   0.9374   0.5866
  -1.000   0.1343   0.01872   0.01228  -0.0742   0.9304   0.7562
  -0.750   0.1893   0.01835   0.01195  -0.0796   0.9215   1.0000
  -0.500   0.2397   0.01845   0.01175  -0.0840   0.9148   1.0000
  -0.250   0.2746   0.01853   0.01162  -0.0855   0.9031   1.0000
   0.000   0.3116   0.01859   0.01152  -0.0873   0.8923   1.0000
   0.250   0.3628   0.01843   0.01121  -0.0915   0.8864   1.0000
   0.500   0.3971   0.01841   0.01108  -0.0925   0.8745   1.0000
   0.750   0.4345   0.01831   0.01089  -0.0941   0.8638   1.0000
   1.000   0.4858   0.01791   0.01043  -0.0979   0.8580   1.0000
   1.250   0.5192   0.01778   0.01025  -0.0986   0.8458   1.0000
   1.500   0.5538   0.01759   0.01003  -0.0993   0.8341   1.0000
   1.750   0.5905   0.01732   0.00973  -0.1003   0.8230   1.0000
   2.000   0.6341   0.01682   0.00923  -0.1023   0.8146   1.0000
   2.250   0.6663   0.01660   0.00899  -0.1024   0.8010   1.0000
   2.500   0.6986   0.01638   0.00876  -0.1025   0.7870   1.0000
   2.750   0.7307   0.01617   0.00856  -0.1026   0.7725   1.0000
   3.000   0.7611   0.01604   0.00841  -0.1023   0.7568   1.0000
   3.250   0.7883   0.01606   0.00842  -0.1016   0.7393   1.0000
   3.500   0.8165   0.01609   0.00847  -0.1011   0.7221   1.0000
   3.750   0.8449   0.01613   0.00849  -0.1006   0.7046   1.0000
   4.000   0.8737   0.01618   0.00851  -0.1002   0.6869   1.0000
   4.250   0.8985   0.01637   0.00870  -0.0991   0.6670   1.0000
   4.500   0.9238   0.01655   0.00890  -0.0981   0.6472   1.0000
   4.750   0.9507   0.01673   0.00902  -0.0974   0.6282   1.0000
   5.000   0.9731   0.01702   0.00936  -0.0961   0.6074   1.0000
   5.250   0.9975   0.01727   0.00960  -0.0950   0.5873   1.0000
   5.500   1.0198   0.01753   0.00991  -0.0935   0.5650   1.0000
   5.750   1.0400   0.01768   0.01001  -0.0915   0.5373   1.0000
   6.000   1.0577   0.01784   0.01012  -0.0891   0.5056   1.0000
   6.250   1.0748   0.01807   0.01030  -0.0868   0.4737   1.0000
   6.500   1.0936   0.01843   0.01068  -0.0849   0.4474   1.0000
   6.750   1.1091   0.01879   0.01101  -0.0824   0.4132   1.0000
   7.000   1.1233   0.01923   0.01141  -0.0798   0.3750   1.0000
   7.250   1.1371   0.01978   0.01189  -0.0772   0.3338   1.0000
   7.500   1.1484   0.02055   0.01249  -0.0743   0.2826   1.0000
   7.750   1.1521   0.02199   0.01339  -0.0706   0.1952   1.0000
   8.000   1.1485   0.02442   0.01496  -0.0663   0.0975   1.0000
   8.250   1.1520   0.02628   0.01664  -0.0627   0.0690   1.0000
   8.500   1.1583   0.02768   0.01806  -0.0593   0.0589   1.0000
   8.750   1.1627   0.02917   0.01956  -0.0559   0.0544   1.0000
   9.000   1.1682   0.03059   0.02113  -0.0527   0.0515   1.0000
   9.250   1.1730   0.03211   0.02274  -0.0497   0.0489   1.0000
   9.500   1.1765   0.03381   0.02448  -0.0469   0.0466   1.0000
   9.750   1.1805   0.03582   0.02650  -0.0442   0.0446   1.0000
  10.000   1.1920   0.03758   0.02838  -0.0422   0.0429   1.0000
  10.250   1.2107   0.03956   0.03045  -0.0409   0.0421   1.0000
  10.500   1.2389   0.04194   0.03299  -0.0405   0.0413   1.0000
  10.750   1.2728   0.04504   0.03634  -0.0409   0.0411   1.0000
  11.000   1.2988   0.04871   0.04036  -0.0407   0.0414   1.0000
  11.250   1.3086   0.05213   0.04416  -0.0388   0.0415   1.0000
  11.500   1.3098   0.05537   0.04776  -0.0362   0.0415   1.0000
  11.750   1.3046   0.05858   0.05130  -0.0334   0.0413   1.0000
  12.000   1.2954   0.06198   0.05503  -0.0307   0.0413   1.0000
  12.250   1.2830   0.06572   0.05908  -0.0284   0.0416   1.0000
  12.500   1.2677   0.06974   0.06339  -0.0267   0.0419   1.0000
  12.750   1.2501   0.07413   0.06805  -0.0256   0.0423   1.0000
  13.000   1.2311   0.07893   0.07310  -0.0253   0.0427   1.0000
  13.250   1.2102   0.08415   0.07855  -0.0260   0.0430   1.0000
  13.500   1.1890   0.08990   0.08450  -0.0275   0.0435   1.0000
  13.750   1.1668   0.09617   0.09096  -0.0299   0.0438   1.0000
  14.000   1.1460   0.10297   0.09791  -0.0330   0.0443   1.0000
  14.250   1.1266   0.11020   0.10526  -0.0366   0.0447   1.0000
  14.500   1.1132   0.11715   0.11233  -0.0399   0.0454   1.0000
  14.750   0.8234   0.14629   0.14221  -0.0614   0.0527   1.0000
  15.000   0.8192   0.15154   0.14746  -0.0636   0.0543   1.0000
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