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GOE 673 AIRFOIL (goe673-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 673 AIRFOIL (goe673-il)
Reynolds number: 200,000
Max Cl/Cd: 73.36 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe673-il-200000-n5.txt
Download as CSV file: xf-goe673-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 673 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3273   0.08623   0.08303  -0.0433   1.0000   0.0141
  -9.500  -0.3351   0.08174   0.07859  -0.0438   1.0000   0.0136
  -9.250  -0.3452   0.07708   0.07399  -0.0441   1.0000   0.0131
  -9.000  -0.3582   0.07233   0.06929  -0.0442   1.0000   0.0127
  -8.750  -0.3749   0.06738   0.06441  -0.0441   1.0000   0.0123
  -8.250  -0.4182   0.04576   0.04273  -0.0589   0.9937   0.0108
  -8.000  -0.4960   0.05674   0.05346  -0.0587   0.9945   0.0108
  -7.750  -0.4805   0.05117   0.04749  -0.0644   0.9884   0.0105
  -7.250  -0.4446   0.04139   0.03697  -0.0717   0.9783   0.0101
  -7.000  -0.4260   0.03658   0.03168  -0.0739   0.9725   0.0100
  -6.500  -0.3725   0.02927   0.02333  -0.0777   0.9654   0.0101
  -6.250  -0.3480   0.02659   0.02019  -0.0781   0.9598   0.0103
  -6.000  -0.3211   0.02309   0.01627  -0.0793   0.9564   0.0116
  -5.750  -0.2891   0.02150   0.01444  -0.0807   0.9538   0.0127
  -5.500  -0.2629   0.01998   0.01270  -0.0805   0.9482   0.0132
  -5.250  -0.2330   0.01858   0.01108  -0.0810   0.9440   0.0139
  -5.000  -0.2017   0.01733   0.00969  -0.0819   0.9408   0.0149
  -4.750  -0.1740   0.01651   0.00876  -0.0820   0.9354   0.0168
  -4.500  -0.1450   0.01579   0.00793  -0.0823   0.9303   0.0184
  -4.250  -0.1145   0.01466   0.00664  -0.0831   0.9266   0.0208
  -4.000  -0.0878   0.01410   0.00594  -0.0830   0.9198   0.0257
  -3.750  -0.0578   0.01352   0.00524  -0.0835   0.9148   0.0339
  -3.500  -0.0313   0.01234   0.00466  -0.0839   0.9089   0.1643
  -3.250  -0.0044   0.01165   0.00438  -0.0842   0.9024   0.2747
  -3.000   0.0229   0.01096   0.00421  -0.0846   0.8969   0.4123
  -2.750   0.0495   0.01069   0.00405  -0.0844   0.8891   0.4705
  -2.500   0.0782   0.01047   0.00384  -0.0845   0.8830   0.5064
  -2.250   0.1050   0.01027   0.00368  -0.0843   0.8747   0.5421
  -2.000   0.1324   0.01007   0.00356  -0.0841   0.8673   0.5822
  -1.750   0.1594   0.00991   0.00345  -0.0838   0.8591   0.6243
  -1.500   0.1860   0.00978   0.00337  -0.0834   0.8502   0.6651
  -1.250   0.2131   0.00964   0.00326  -0.0830   0.8422   0.7035
  -1.000   0.2388   0.00952   0.00321  -0.0823   0.8325   0.7428
  -0.750   0.2639   0.00939   0.00315  -0.0815   0.8229   0.7828
  -0.500   0.2884   0.00926   0.00309  -0.0804   0.8135   0.8251
  -0.250   0.3131   0.00916   0.00306  -0.0792   0.8032   0.8733
   0.000   0.3426   0.00910   0.00301  -0.0792   0.7924   0.9242
   0.250   0.3776   0.00907   0.00293  -0.0806   0.7815   0.9621
   0.500   0.4154   0.00904   0.00284  -0.0829   0.7700   0.9956
   0.750   0.4433   0.00908   0.00279  -0.0830   0.7577   1.0000
   1.000   0.4700   0.00914   0.00278  -0.0828   0.7447   1.0000
   1.250   0.4967   0.00921   0.00278  -0.0827   0.7312   1.0000
   1.500   0.5234   0.00930   0.00282  -0.0825   0.7173   1.0000
   1.750   0.5502   0.00940   0.00286  -0.0824   0.7030   1.0000
   2.000   0.5769   0.00952   0.00292  -0.0822   0.6884   1.0000
   2.250   0.6035   0.00965   0.00301  -0.0820   0.6737   1.0000
   2.500   0.6301   0.00979   0.00311  -0.0818   0.6584   1.0000
   2.750   0.6565   0.00995   0.00324  -0.0816   0.6427   1.0000
   3.000   0.6828   0.01013   0.00341  -0.0814   0.6268   1.0000
   3.250   0.7090   0.01031   0.00358  -0.0812   0.6113   1.0000
   3.500   0.7353   0.01050   0.00377  -0.0810   0.5964   1.0000
   3.750   0.7615   0.01071   0.00399  -0.0808   0.5818   1.0000
   4.000   0.7876   0.01092   0.00426  -0.0805   0.5673   1.0000
   4.250   0.8137   0.01114   0.00453  -0.0803   0.5530   1.0000
   4.500   0.8378   0.01142   0.00478  -0.0796   0.5250   1.0000
   4.750   0.8569   0.01195   0.00502  -0.0780   0.4614   1.0000
   5.000   0.8736   0.01273   0.00543  -0.0761   0.3802   1.0000
   5.250   0.8837   0.01420   0.00612  -0.0735   0.2432   1.0000
   5.500   0.8846   0.01688   0.00760  -0.0699   0.0403   1.0000
   5.750   0.9035   0.01781   0.00848  -0.0686   0.0231   1.0000
   6.000   0.9244   0.01851   0.00934  -0.0674   0.0192   1.0000
   6.250   0.9433   0.01936   0.01033  -0.0660   0.0166   1.0000
   6.500   0.9554   0.02076   0.01190  -0.0635   0.0138   1.0000
   6.750   0.9715   0.02173   0.01302  -0.0618   0.0130   1.0000
   7.000   0.9853   0.02290   0.01431  -0.0596   0.0123   1.0000
   7.250   0.9982   0.02419   0.01570  -0.0573   0.0117   1.0000
   7.500   1.0114   0.02556   0.01717  -0.0551   0.0112   1.0000
   7.750   1.0258   0.02677   0.01847  -0.0532   0.0103   1.0000
   8.000   1.0402   0.02789   0.01966  -0.0514   0.0093   1.0000
   8.250   1.0546   0.02940   0.02124  -0.0497   0.0087   1.0000
   8.500   1.0736   0.03174   0.02368  -0.0486   0.0083   1.0000
   8.750   1.0991   0.03503   0.02717  -0.0486   0.0080   1.0000
   9.000   1.1172   0.03720   0.02960  -0.0473   0.0079   1.0000
   9.250   1.1325   0.03966   0.03235  -0.0457   0.0078   1.0000
   9.500   1.1438   0.04236   0.03544  -0.0436   0.0077   1.0000
   9.750   1.1498   0.04516   0.03855  -0.0409   0.0077   1.0000
  10.000   1.1508   0.04792   0.04162  -0.0378   0.0076   1.0000
  10.250   1.1484   0.05053   0.04452  -0.0345   0.0075   1.0000
  10.500   1.1438   0.05321   0.04749  -0.0313   0.0073   1.0000
  10.750   1.1369   0.05612   0.05067  -0.0284   0.0071   1.0000
  11.000   1.1273   0.05934   0.05415  -0.0260   0.0069   1.0000
  11.250   1.1161   0.06279   0.05785  -0.0241   0.0067   1.0000
  11.500   1.1026   0.06671   0.06200  -0.0228   0.0067   1.0000
  11.750   1.0874   0.07102   0.06653  -0.0222   0.0066   1.0000
  12.000   1.0709   0.07579   0.07151  -0.0225   0.0066   1.0000
  12.250   1.0533   0.08111   0.07703  -0.0236   0.0066   1.0000
  12.500   1.0347   0.08702   0.08313  -0.0257   0.0066   1.0000
  12.750   1.0155   0.09358   0.08986  -0.0287   0.0067   1.0000
  13.000   0.9962   0.10079   0.09722  -0.0326   0.0068   1.0000
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