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GOE 364 AIRFOIL (goe364-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 364 AIRFOIL (goe364-il)
Reynolds number: 50,000
Max Cl/Cd: 34.78 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe364-il-50000-n5.txt
Download as CSV file: xf-goe364-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 364 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2227   0.11705   0.11085  -0.0316   1.0000   0.0824
  -8.750  -0.2308   0.11594   0.10987  -0.0295   1.0000   0.0840
  -8.500  -0.2425   0.11526   0.10933  -0.0271   1.0000   0.0853
  -8.250  -0.2461   0.11398   0.10814  -0.0276   0.9967   0.0873
  -8.000  -0.2385   0.11268   0.10686  -0.0357   0.9835   0.0897
  -7.750  -0.2313   0.11138   0.10557  -0.0453   0.9670   0.0903
  -7.500  -0.1997   0.10339   0.09758  -0.0409   0.9676   0.0940
  -7.250  -0.1820   0.10004   0.09423  -0.0443   0.9583   0.0992
  -7.000  -0.1724   0.09825   0.09244  -0.0525   0.9425   0.1039
  -6.750  -0.1554   0.09450   0.08869  -0.0585   0.9317   0.1060
  -6.500  -0.1377   0.09015   0.08435  -0.0566   0.9234   0.1099
  -6.250  -0.1142   0.08655   0.08071  -0.0617   0.9147   0.1156
  -6.000  -0.0949   0.08494   0.07894  -0.0740   0.8991   0.1207
  -5.500  -0.0555   0.07660   0.07062  -0.0738   0.8821   0.1326
  -5.250  -0.0369   0.07337   0.06732  -0.0779   0.8707   0.1393
  -5.000  -0.0190   0.07046   0.06439  -0.0785   0.8606   0.1470
  -4.500   0.0272   0.06485   0.05852  -0.0858   0.8415   0.1678
  -4.250   0.0501   0.06130   0.05493  -0.0871   0.8344   0.1750
  -4.000   0.0690   0.05886   0.05243  -0.0882   0.8244   0.1914
  -3.750   0.0898   0.05639   0.04990  -0.0888   0.8159   0.2111
  -3.250   0.1818   0.04734   0.03953  -0.1012   0.7996   0.0874
  -3.000   0.2090   0.04495   0.03689  -0.1022   0.7908   0.0858
  -2.750   0.2378   0.04274   0.03437  -0.1031   0.7826   0.0850
  -2.500   0.2660   0.04064   0.03192  -0.1036   0.7738   0.0826
  -2.250   0.2967   0.03858   0.02938  -0.1042   0.7658   0.0797
  -2.000   0.3259   0.03693   0.02723  -0.1041   0.7569   0.0778
  -1.750   0.3536   0.03557   0.02564  -0.1041   0.7485   0.0790
  -1.500   0.3810   0.03444   0.02426  -0.1039   0.7395   0.0807
  -1.250   0.4087   0.03337   0.02289  -0.1036   0.7308   0.0812
  -1.000   0.4382   0.03234   0.02154  -0.1034   0.7222   0.0811
  -0.750   0.4657   0.03156   0.02049  -0.1029   0.7130   0.0815
  -0.500   0.4960   0.03075   0.01942  -0.1028   0.7048   0.0826
  -0.250   0.5209   0.03034   0.01882  -0.1019   0.6952   0.0854
   0.000   0.5552   0.02973   0.01790  -0.1023   0.6875   0.0888
   0.250   0.5810   0.02949   0.01748  -0.1016   0.6775   0.0906
   0.500   0.6138   0.02888   0.01676  -0.1019   0.6702   0.0936
   0.750   0.6356   0.02887   0.01668  -0.1008   0.6600   0.0971
   1.000   0.6673   0.02850   0.01612  -0.1008   0.6531   0.1045
   1.250   0.6870   0.02862   0.01629  -0.0995   0.6427   0.1138
   1.500   0.7191   0.02823   0.01583  -0.0997   0.6362   0.1297
   1.750   0.7386   0.02833   0.01616  -0.0986   0.6258   0.1710
   2.000   0.7849   0.02647   0.01567  -0.1014   0.6193   1.0000
   2.250   0.8015   0.02713   0.01615  -0.0996   0.6085   1.0000
   2.500   0.8292   0.02725   0.01601  -0.0991   0.6002   1.0000
   2.750   0.8501   0.02759   0.01619  -0.0977   0.5893   1.0000
   3.000   0.8705   0.02795   0.01642  -0.0963   0.5785   1.0000
   3.250   0.9003   0.02788   0.01614  -0.0959   0.5701   1.0000
   3.500   0.9160   0.02847   0.01668  -0.0940   0.5586   1.0000
   3.750   0.9397   0.02873   0.01683  -0.0931   0.5497   1.0000
   4.000   0.9618   0.02908   0.01709  -0.0919   0.5404   1.0000
   4.250   0.9808   0.02961   0.01758  -0.0905   0.5311   1.0000
   4.500   1.0067   0.02979   0.01766  -0.0899   0.5231   1.0000
   4.750   1.0225   0.03049   0.01837  -0.0882   0.5133   1.0000
   5.000   1.0516   0.03051   0.01828  -0.0879   0.5058   1.0000
   5.250   1.0643   0.03136   0.01917  -0.0858   0.4955   1.0000
   5.500   1.0905   0.03155   0.01930  -0.0853   0.4877   1.0000
   5.750   1.1062   0.03224   0.02002  -0.0835   0.4777   1.0000
   6.000   1.1265   0.03273   0.02050  -0.0824   0.4690   1.0000
   6.250   1.1477   0.03318   0.02095  -0.0813   0.4599   1.0000
   6.500   1.1628   0.03396   0.02177  -0.0795   0.4505   1.0000
   6.750   1.1886   0.03420   0.02196  -0.0790   0.4420   1.0000
   7.000   1.1979   0.03526   0.02311  -0.0766   0.4319   1.0000
   7.250   1.2286   0.03532   0.02311  -0.0766   0.4241   1.0000
   7.500   1.2310   0.03674   0.02466  -0.0736   0.4137   1.0000
   7.750   1.2557   0.03712   0.02501  -0.0730   0.4058   1.0000
   8.000   1.2598   0.03844   0.02645  -0.0703   0.3961   1.0000
   8.250   1.2778   0.03912   0.02717  -0.0690   0.3881   1.0000
   8.500   1.2818   0.04044   0.02859  -0.0662   0.3792   1.0000
   8.750   1.2960   0.04134   0.02953  -0.0646   0.3716   1.0000
   9.000   1.2975   0.04292   0.03122  -0.0620   0.3633   1.0000
   9.250   1.3128   0.04378   0.03215  -0.0606   0.3563   1.0000
   9.500   1.3065   0.04596   0.03447  -0.0578   0.3481   1.0000
   9.750   1.3285   0.04640   0.03492  -0.0570   0.3417   1.0000
  10.000   1.3070   0.04994   0.03865  -0.0539   0.3339   1.0000
  10.250   1.3409   0.04936   0.03805  -0.0535   0.3279   1.0000
  10.500   1.2993   0.05503   0.04395  -0.0506   0.3198   1.0000
  10.750   1.3264   0.05480   0.04377  -0.0498   0.3140   1.0000
  11.000   1.2809   0.06191   0.05105  -0.0485   0.3059   1.0000
  11.250   1.2993   0.06239   0.05162  -0.0475   0.3000   1.0000
  11.500   1.2367   0.07308   0.06245  -0.0483   0.2903   1.0000
  11.750   1.2577   0.07311   0.06257  -0.0473   0.2853   1.0000
  12.000   1.1846   0.08724   0.07679  -0.0507   0.2732   1.0000
  12.250   1.2154   0.08552   0.07517  -0.0489   0.2697   1.0000
  12.500   1.2680   0.08066   0.07038  -0.0462   0.2675   1.0000
  12.750   1.1768   0.09873   0.08854  -0.0519   0.2538   1.0000
  13.000   1.2182   0.09495   0.08486  -0.0492   0.2519   1.0000
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