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GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 630 AIRFOIL (goe630-il)
Reynolds number: 50,000
Max Cl/Cd: 28.26 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe630-il-50000-n5.txt
Download as CSV file: xf-goe630-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 630 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  -0.0411   0.10988   0.10339  -0.0766   0.9184   0.1062
  -8.250  -0.0255   0.10714   0.10061  -0.0809   0.9133   0.1103
  -8.000  -0.0312   0.10696   0.10048  -0.0828   0.9014   0.1128
  -7.750  -0.0408   0.10726   0.10081  -0.0855   0.8898   0.1137
  -7.500  -0.0223   0.10247   0.09603  -0.0867   0.8842   0.1150
  -7.250   0.0139   0.09678   0.09027  -0.0878   0.8820   0.1202
  -7.000   0.0162   0.09517   0.08867  -0.0877   0.8723   0.1248
  -6.750   0.0161   0.09453   0.08802  -0.0926   0.8628   0.1297
  -6.500   0.0065   0.09504   0.08852  -0.0964   0.8490   0.1307
  -6.250   0.0352   0.08864   0.08214  -0.0933   0.8469   0.1336
  -6.000   0.0389   0.08666   0.08018  -0.0914   0.8371   0.1363
  -5.750   0.0553   0.08397   0.07745  -0.0938   0.8307   0.1413
  -5.500   0.0511   0.08397   0.07740  -0.0976   0.8179   0.1470
  -5.250   0.0723   0.08007   0.07346  -0.1002   0.8129   0.1492
  -4.750   0.1005   0.07667   0.06989  -0.1058   0.7959   0.1647
  -4.500   0.0985   0.07404   0.06737  -0.1003   0.7859   0.1665
  -4.250   0.1196   0.07099   0.06429  -0.1001   0.7806   0.1726
  -4.000   0.1307   0.06988   0.06304  -0.1039   0.7696   0.1823
  -3.500   0.1972   0.05974   0.05217  -0.1154   0.7556   0.0968
  -3.250   0.2196   0.05717   0.04950  -0.1163   0.7484   0.0945
  -3.000   0.2588   0.05376   0.04582  -0.1205   0.7445   0.0935
  -2.750   0.2681   0.05240   0.04433  -0.1193   0.7328   0.0927
  -2.500   0.3084   0.04904   0.04058  -0.1230   0.7285   0.0896
  -2.250   0.3240   0.04734   0.03857  -0.1226   0.7177   0.0875
  -2.000   0.3640   0.04436   0.03499  -0.1254   0.7127   0.0855
  -1.750   0.3809   0.04335   0.03381  -0.1243   0.7030   0.0864
  -1.500   0.4119   0.04183   0.03206  -0.1251   0.6967   0.0887
  -1.250   0.4363   0.04069   0.03064  -0.1248   0.6886   0.0904
  -1.000   0.4633   0.03943   0.02904  -0.1247   0.6807   0.0910
  -0.750   0.5044   0.03758   0.02675  -0.1262   0.6767   0.0921
  -0.500   0.5157   0.03745   0.02642  -0.1239   0.6649   0.0934
  -0.250   0.5563   0.03608   0.02454  -0.1252   0.6605   0.0980
   0.000   0.5669   0.03610   0.02450  -0.1227   0.6488   0.1003
   0.250   0.6056   0.03492   0.02309  -0.1237   0.6442   0.1041
   0.500   0.6198   0.03515   0.02317  -0.1218   0.6330   0.1076
   0.750   0.6607   0.03417   0.02189  -0.1231   0.6281   0.1159
   1.000   0.6744   0.03449   0.02219  -0.1211   0.6172   0.1213
   1.250   0.7123   0.03368   0.02120  -0.1220   0.6121   0.1330
   1.500   0.7257   0.03412   0.02164  -0.1201   0.6017   0.1438
   1.750   0.7616   0.03342   0.02092  -0.1208   0.5963   0.1681
   2.000   0.7774   0.03373   0.02137  -0.1193   0.5866   0.2043
   2.250   0.8165   0.03165   0.02086  -0.1210   0.5809   1.0000
   2.500   0.8344   0.03226   0.02117  -0.1195   0.5727   1.0000
   2.750   0.8586   0.03255   0.02119  -0.1187   0.5656   1.0000
   3.000   0.8862   0.03271   0.02110  -0.1184   0.5595   1.0000
   3.250   0.8971   0.03363   0.02190  -0.1162   0.5506   1.0000
   3.500   0.9342   0.03338   0.02141  -0.1170   0.5463   1.0000
   3.750   0.9333   0.03490   0.02291  -0.1135   0.5363   1.0000
   4.000   0.9656   0.03487   0.02269  -0.1138   0.5315   1.0000
   4.250   0.9722   0.03613   0.02390  -0.1112   0.5234   1.0000
   4.500   0.9925   0.03672   0.02441  -0.1102   0.5172   1.0000
   4.750   1.0304   0.03646   0.02398  -0.1112   0.5136   1.0000
   5.000   1.0170   0.03894   0.02652  -0.1069   0.5039   1.0000
   5.250   1.0456   0.03909   0.02657  -0.1067   0.4994   1.0000
   5.500   1.0680   0.03966   0.02708  -0.1061   0.4945   1.0000
   5.750   1.0571   0.04231   0.02979  -0.1026   0.4856   1.0000
   6.000   1.0883   0.04231   0.02971  -0.1027   0.4822   1.0000
   6.500   1.0811   0.04733   0.03483  -0.0979   0.4679   1.0000
   6.750   1.1149   0.04703   0.03446  -0.0980   0.4652   1.0000
   7.250   1.0921   0.05407   0.04164  -0.0936   0.4499   1.0000
   7.500   1.1241   0.05382   0.04137  -0.0934   0.4480   1.0000
   8.000   1.0613   0.06652   0.05427  -0.0901   0.4284   1.0000
  10.000   1.0400   0.09726   0.08547  -0.0879   0.3827   1.0000
  10.250   1.0059   0.10539   0.09370  -0.0889   0.3738   1.0000
  10.500   1.0154   0.10772   0.09609  -0.0887   0.3698   1.0000
  10.750   1.0350   0.10873   0.09716  -0.0882   0.3671   1.0000
  11.250   1.0188   0.11809   0.10667  -0.0893   0.3553   1.0000
  11.500   1.0340   0.11967   0.10831  -0.0890   0.3520   1.0000
  11.750   1.0560   0.12039   0.10909  -0.0885   0.3497   1.0000
  12.000   1.0281   0.12765   0.11645  -0.0902   0.3413   1.0000
  12.250   1.0388   0.12983   0.11872  -0.0902   0.3372   1.0000
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