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GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 371 AIRFOIL (goe371-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.88 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe371-il-1000000-n5.txt
Download as CSV file: xf-goe371-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 371 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3403   0.10309   0.10145  -0.0268   1.0000   0.0039
  -9.250  -0.3359   0.10049   0.09887  -0.0273   1.0000   0.0041
  -9.000  -0.3352   0.09709   0.09550  -0.0278   1.0000   0.0040
  -8.750  -0.3274   0.09350   0.09192  -0.0302   0.9992   0.0040
  -8.500  -0.3170   0.08997   0.08840  -0.0329   0.9917   0.0043
  -8.250  -0.3057   0.08583   0.08426  -0.0368   0.9839   0.0045
  -8.000  -0.2905   0.08106   0.07948  -0.0424   0.9742   0.0047
  -7.750  -0.2680   0.07434   0.07274  -0.0524   0.9632   0.0050
  -7.500  -0.2382   0.06482   0.06317  -0.0684   0.9442   0.0054
  -7.250  -0.2101   0.06156   0.05981  -0.0749   0.9211   0.0057
  -7.000  -0.1957   0.05717   0.05528  -0.0800   0.8891   0.0059
  -6.750  -0.1826   0.05305   0.05101  -0.0839   0.8600   0.0062
  -6.500  -0.1687   0.04664   0.04442  -0.0899   0.8368   0.0068
  -6.250  -0.1760   0.01430   0.01012  -0.1039   0.8185   0.0095
  -6.000  -0.1554   0.01154   0.00681  -0.1032   0.8062   0.0109
  -5.500  -0.1000   0.01236   0.00770  -0.1028   0.7846   0.0128
  -5.250  -0.0755   0.01109   0.00612  -0.1023   0.7763   0.0146
  -5.000  -0.0485   0.01097   0.00593  -0.1021   0.7683   0.0152
  -4.750  -0.0208   0.01128   0.00624  -0.1019   0.7605   0.0157
  -4.500   0.0068   0.01157   0.00653  -0.1018   0.7528   0.0163
  -4.250   0.0341   0.01154   0.00644  -0.1016   0.7469   0.0173
  -4.000   0.0608   0.01116   0.00593  -0.1013   0.7405   0.0185
  -3.750   0.0878   0.01092   0.00557  -0.1011   0.7344   0.0195
  -3.500   0.1151   0.01080   0.00538  -0.1009   0.7281   0.0201
  -3.000   0.1681   0.00985   0.00421  -0.1003   0.7145   0.0215
  -2.750   0.1949   0.00953   0.00385  -0.1001   0.7081   0.0220
  -2.500   0.2220   0.00933   0.00361  -0.0999   0.7026   0.0227
  -2.250   0.2492   0.00915   0.00339  -0.0997   0.6963   0.0234
  -2.000   0.2761   0.00890   0.00308  -0.0994   0.6902   0.0240
  -1.750   0.3032   0.00865   0.00279  -0.0992   0.6830   0.0245
  -1.500   0.3301   0.00844   0.00252  -0.0989   0.6748   0.0249
  -1.250   0.3569   0.00823   0.00226  -0.0986   0.6643   0.0252
  -1.000   0.3836   0.00806   0.00203  -0.0983   0.6513   0.0254
  -0.750   0.4098   0.00793   0.00181  -0.0979   0.6313   0.0256
  -0.500   0.4347   0.00795   0.00166  -0.0972   0.5874   0.0260
  -0.250   0.4588   0.00809   0.00157  -0.0965   0.5371   0.0262
   0.000   0.4839   0.00815   0.00147  -0.0959   0.5066   0.0263
   0.250   0.5098   0.00817   0.00139  -0.0955   0.4872   0.0264
   0.500   0.5362   0.00817   0.00132  -0.0951   0.4725   0.0266
   0.750   0.5627   0.00818   0.00127  -0.0948   0.4595   0.0270
   1.000   0.5894   0.00820   0.00125  -0.0945   0.4481   0.0275
   1.250   0.6160   0.00824   0.00125  -0.0943   0.4377   0.0281
   1.500   0.6426   0.00829   0.00127  -0.0940   0.4279   0.0287
   1.750   0.6694   0.00830   0.00124  -0.0937   0.4190   0.0307
   2.000   0.6960   0.00836   0.00127  -0.0935   0.4104   0.0320
   2.250   0.7228   0.00840   0.00131  -0.0932   0.4027   0.0335
   2.500   0.7495   0.00847   0.00136  -0.0930   0.3948   0.0349
   2.750   0.7761   0.00853   0.00142  -0.0927   0.3864   0.0372
   3.000   0.8004   0.00801   0.00164  -0.0923   0.3798   0.4142
   3.500   0.8644   0.00717   0.00196  -0.0947   0.3481   1.0000
   3.750   0.8897   0.00736   0.00208  -0.0942   0.3292   1.0000
   4.000   0.9134   0.00771   0.00225  -0.0935   0.2918   1.0000
   4.250   0.9353   0.00823   0.00252  -0.0925   0.2424   1.0000
   4.500   0.9587   0.00862   0.00277  -0.0918   0.2133   1.0000
   4.750   0.9829   0.00893   0.00299  -0.0912   0.1951   1.0000
   5.000   1.0072   0.00923   0.00322  -0.0906   0.1774   1.0000
   5.250   1.0315   0.00952   0.00344  -0.0900   0.1627   1.0000
   5.500   1.0558   0.00981   0.00367  -0.0894   0.1486   1.0000
   5.750   1.0799   0.01012   0.00391  -0.0888   0.1338   1.0000
   6.000   1.1029   0.01052   0.00420  -0.0880   0.1122   1.0000
   6.250   1.1230   0.01120   0.00465  -0.0869   0.0729   1.0000
   6.500   1.1449   0.01171   0.00506  -0.0859   0.0535   1.0000
   6.750   1.1670   0.01217   0.00546  -0.0851   0.0398   1.0000
   7.000   1.1865   0.01289   0.00603  -0.0838   0.0148   1.0000
   7.250   1.2089   0.01331   0.00646  -0.0829   0.0113   1.0000
   7.500   1.2315   0.01370   0.00688  -0.0820   0.0093   1.0000
   7.750   1.2541   0.01406   0.00729  -0.0812   0.0083   1.0000
   8.000   1.2759   0.01449   0.00774  -0.0803   0.0074   1.0000
   8.250   1.2966   0.01502   0.00830  -0.0792   0.0063   1.0000
   8.500   1.3182   0.01542   0.00875  -0.0783   0.0060   1.0000
   8.750   1.3393   0.01585   0.00922  -0.0773   0.0054   1.0000
   9.000   1.3596   0.01634   0.00974  -0.0762   0.0049   1.0000
   9.250   1.3785   0.01692   0.01037  -0.0748   0.0045   1.0000
   9.500   1.3961   0.01759   0.01111  -0.0733   0.0042   1.0000
   9.750   1.4146   0.01814   0.01172  -0.0719   0.0041   1.0000
  10.000   1.4323   0.01871   0.01235  -0.0704   0.0038   1.0000
  10.250   1.4485   0.01935   0.01306  -0.0688   0.0036   1.0000
  10.500   1.4625   0.02000   0.01378  -0.0667   0.0035   1.0000
  10.750   1.4754   0.02062   0.01445  -0.0644   0.0033   1.0000
  11.000   1.4871   0.02131   0.01522  -0.0620   0.0031   1.0000
  11.250   1.4983   0.02204   0.01600  -0.0597   0.0030   1.0000
  11.500   1.5059   0.02303   0.01708  -0.0570   0.0028   1.0000
  11.750   1.5101   0.02428   0.01843  -0.0540   0.0026   1.0000
  12.000   1.5195   0.02521   0.01944  -0.0519   0.0026   1.0000
  12.250   1.5266   0.02634   0.02066  -0.0497   0.0025   1.0000
  12.500   1.5312   0.02772   0.02215  -0.0474   0.0025   1.0000
  12.750   1.5395   0.02887   0.02339  -0.0457   0.0024   1.0000
  13.000   1.5418   0.03056   0.02519  -0.0437   0.0024   1.0000
  13.250   1.5452   0.03226   0.02699  -0.0420   0.0023   1.0000
  13.500   1.5478   0.03413   0.02898  -0.0405   0.0022   1.0000
  13.750   1.5465   0.03648   0.03146  -0.0391   0.0022   1.0000
  14.000   1.5470   0.03878   0.03387  -0.0380   0.0021   1.0000
  14.250   1.5452   0.04143   0.03663  -0.0372   0.0021   1.0000
  14.500   1.5449   0.04404   0.03935  -0.0366   0.0020   1.0000
  14.750   1.5400   0.04729   0.04273  -0.0363   0.0020   1.0000
  15.000   1.5331   0.05098   0.04654  -0.0363   0.0020   1.0000
  15.250   1.5343   0.05381   0.04946  -0.0365   0.0019   1.0000
  15.500   1.5209   0.05882   0.05463  -0.0374   0.0019   1.0000
  15.750   1.5127   0.06342   0.05936  -0.0387   0.0019   1.0000
  16.000   1.5062   0.06801   0.06407  -0.0402   0.0019   1.0000
  16.250   1.4963   0.07332   0.06950  -0.0421   0.0018   1.0000
  16.500   1.4820   0.07954   0.07587  -0.0445   0.0018   1.0000
  16.750   1.4742   0.08483   0.08126  -0.0468   0.0018   1.0000
  17.000   1.4551   0.09223   0.08882  -0.0500   0.0018   1.0000
  17.250   1.4451   0.09817   0.09486  -0.0527   0.0018   1.0000
  17.500   1.4250   0.10622   0.10306  -0.0565   0.0018   1.0000
  17.750   1.4072   0.11407   0.11105  -0.0604   0.0018   1.0000
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