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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.49 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe379-il-1000000-n5.txt
Download as CSV file: xf-goe379-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2243   0.11672   0.11521  -0.0279   1.0000   0.0036
 -10.750  -0.2209   0.11356   0.11206  -0.0283   1.0000   0.0035
 -10.500  -0.3163   0.12376   0.12212  -0.0211   1.0000   0.0035
 -10.250  -0.3103   0.12087   0.11923  -0.0220   1.0000   0.0035
 -10.000  -0.3090   0.11683   0.11521  -0.0224   1.0000   0.0030
  -9.750  -0.3046   0.11391   0.11231  -0.0231   1.0000   0.0023
  -9.250  -0.2945   0.10782   0.10625  -0.0246   1.0000   0.0028
  -9.000  -0.2875   0.10508   0.10353  -0.0254   1.0000   0.0034
  -8.750  -0.2809   0.10307   0.10153  -0.0262   1.0000   0.0036
  -8.500  -0.2719   0.10021   0.09869  -0.0278   0.9926   0.0037
  -8.250  -0.2557   0.09755   0.09603  -0.0319   0.9817   0.0039
  -8.000  -0.2357   0.09348   0.09194  -0.0372   0.9702   0.0039
  -7.750  -0.2082   0.08828   0.08672  -0.0447   0.9599   0.0038
  -7.500  -0.1734   0.08351   0.08190  -0.0546   0.9466   0.0039
  -7.250  -0.1426   0.07851   0.07680  -0.0637   0.9199   0.0039
  -7.000  -0.1280   0.07544   0.07361  -0.0670   0.8898   0.0039
  -6.750  -0.1191   0.07265   0.07072  -0.0686   0.8645   0.0039
  -6.500  -0.1100   0.06980   0.06778  -0.0700   0.8445   0.0039
  -6.250  -0.1056   0.06525   0.06317  -0.0713   0.8282   0.0036
  -6.000  -0.0957   0.06177   0.05960  -0.0733   0.8106   0.0034
  -5.750  -0.0822   0.05871   0.05646  -0.0754   0.7938   0.0033
  -5.500  -0.0667   0.05528   0.05294  -0.0778   0.7787   0.0032
  -5.250  -0.0490   0.05183   0.04939  -0.0803   0.7634   0.0031
  -5.000  -0.0295   0.04839   0.04584  -0.0826   0.7458   0.0030
  -4.750  -0.0080   0.04498   0.04229  -0.0848   0.7323   0.0030
  -4.500   0.0155   0.04057   0.03773  -0.0873   0.7200   0.0029
  -4.250   0.0402   0.03594   0.03292  -0.0893   0.7091   0.0029
  -4.000   0.0638   0.02372   0.02015  -0.0908   0.7026   0.0040
  -3.750   0.0886   0.02315   0.01948  -0.0907   0.6903   0.0041
  -3.500   0.1139   0.02342   0.01968  -0.0907   0.6764   0.0044
  -3.250   0.1386   0.02276   0.01891  -0.0906   0.6631   0.0049
  -3.000   0.1630   0.02065   0.01658  -0.0900   0.6509   0.0060
  -2.750   0.1873   0.01860   0.01429  -0.0892   0.6374   0.0083
  -2.500   0.2016   0.00439   0.00019  -0.0837   0.6019   0.0104
  -2.000   0.2645   0.01788   0.01322  -0.0883   0.5893   0.0183
   0.000   0.4637   0.00894   0.00242  -0.0821   0.4989   0.0175
   0.250   0.4888   0.00857   0.00188  -0.0813   0.4864   0.0159
   0.750   0.5404   0.00834   0.00142  -0.0802   0.4620   0.0131
   1.000   0.5664   0.00832   0.00134  -0.0798   0.4496   0.0124
   1.250   0.5923   0.00832   0.00128  -0.0794   0.4363   0.0119
   1.500   0.6180   0.00833   0.00123  -0.0790   0.4227   0.0116
   1.750   0.6438   0.00836   0.00119  -0.0785   0.4087   0.0115
   2.000   0.6695   0.00842   0.00115  -0.0781   0.3954   0.0119
   2.250   0.6953   0.00848   0.00116  -0.0777   0.3831   0.0166
   2.500   0.7207   0.00854   0.00124  -0.0773   0.3702   0.0470
   2.750   0.7462   0.00862   0.00135  -0.0770   0.3585   0.0645
   3.250   0.7857   0.00763   0.00171  -0.0742   0.3434   0.7370
   3.500   0.8861   0.00741   0.00195  -0.0912   0.3274   1.0000
   3.750   0.9108   0.00755   0.00206  -0.0907   0.3206   1.0000
   4.000   0.9355   0.00770   0.00221  -0.0901   0.3120   1.0000
   4.250   0.9563   0.00817   0.00243  -0.0890   0.2667   1.0000
   4.500   0.9724   0.00907   0.00285  -0.0871   0.1809   1.0000
   4.750   0.9887   0.00995   0.00336  -0.0852   0.1125   1.0000
   5.000   1.0011   0.01125   0.00419  -0.0826   0.0054   1.0000
   5.250   1.0243   0.01150   0.00446  -0.0818   0.0039   1.0000
   5.500   1.0473   0.01178   0.00477  -0.0809   0.0027   1.0000
   5.750   1.0695   0.01211   0.00517  -0.0799   0.0022   1.0000
   6.000   1.0919   0.01242   0.00555  -0.0790   0.0017   1.0000
   6.250   1.1129   0.01286   0.00606  -0.0778   0.0015   1.0000
   6.500   1.1332   0.01335   0.00661  -0.0764   0.0014   1.0000
   6.750   1.1524   0.01393   0.00728  -0.0749   0.0014   1.0000
   7.000   1.1709   0.01456   0.00799  -0.0733   0.0014   1.0000
   7.250   1.1874   0.01532   0.00885  -0.0713   0.0014   1.0000
   7.500   1.2021   0.01620   0.00982  -0.0690   0.0014   1.0000
   7.750   1.2151   0.01714   0.01086  -0.0665   0.0014   1.0000
   8.000   1.2255   0.01822   0.01204  -0.0636   0.0014   1.0000
   8.250   1.2361   0.01921   0.01311  -0.0609   0.0014   1.0000
   8.500   1.2432   0.02042   0.01440  -0.0575   0.0014   1.0000
   8.750   1.2473   0.02156   0.01562  -0.0536   0.0015   1.0000
   9.000   1.2488   0.02302   0.01717  -0.0494   0.0015   1.0000
   9.250   1.2551   0.02435   0.01859  -0.0464   0.0015   1.0000
   9.500   1.2624   0.02583   0.02016  -0.0436   0.0016   1.0000
   9.750   1.2709   0.02757   0.02201  -0.0411   0.0016   1.0000
  10.000   1.2808   0.02941   0.02406  -0.0389   0.0017   1.0000
  10.250   1.2917   0.03183   0.02665  -0.0369   0.0017   1.0000
  10.500   1.3006   0.03416   0.02914  -0.0348   0.0018   1.0000
  10.750   1.3060   0.03692   0.03209  -0.0324   0.0019   1.0000
  11.000   1.3051   0.04365   0.03918  -0.0299   0.0022   1.0000
  11.250   1.2997   0.04622   0.04193  -0.0271   0.0022   1.0000
  11.500   1.2912   0.04908   0.04496  -0.0244   0.0022   1.0000
  11.750   1.2821   0.05181   0.04786  -0.0223   0.0022   1.0000
  12.000   1.2704   0.05527   0.05149  -0.0206   0.0022   1.0000
  12.250   1.2579   0.05871   0.05509  -0.0195   0.0022   1.0000
  12.500   1.2444   0.06258   0.05913  -0.0189   0.0022   1.0000
  12.750   1.2308   0.06668   0.06338  -0.0190   0.0022   1.0000
  13.000   1.2152   0.07130   0.06816  -0.0196   0.0022   1.0000
  13.250   1.2011   0.07583   0.07283  -0.0209   0.0022   1.0000
  13.500   1.1855   0.08113   0.07827  -0.0226   0.0022   1.0000
  13.750   1.1693   0.08683   0.08410  -0.0248   0.0022   1.0000
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