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GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 617 AIRFOIL (goe617-il)
Reynolds number: 200,000
Max Cl/Cd: 63.03 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe617-il-200000-n5.txt
Download as CSV file: xf-goe617-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 617 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.8202   0.05842   0.05365  -0.0747   1.0000   0.0287
 -14.000  -0.8472   0.05222   0.04721  -0.0779   1.0000   0.0287
 -13.750  -0.8531   0.04941   0.04434  -0.0784   1.0000   0.0291
 -13.500  -0.8631   0.04651   0.04132  -0.0782   1.0000   0.0293
 -13.250  -0.8701   0.04427   0.03898  -0.0772   1.0000   0.0297
 -13.000  -0.8759   0.04240   0.03700  -0.0755   1.0000   0.0302
 -12.750  -0.8857   0.04032   0.03476  -0.0729   1.0000   0.0306
 -12.500  -0.8942   0.03858   0.03286  -0.0696   1.0000   0.0312
 -12.250  -0.9027   0.03704   0.03115  -0.0656   1.0000   0.0318
 -12.000  -0.9124   0.03562   0.02953  -0.0609   1.0000   0.0323
 -11.750  -0.9232   0.03434   0.02804  -0.0555   1.0000   0.0329
 -11.500  -0.9295   0.03314   0.02663  -0.0505   1.0000   0.0334
 -11.250  -0.9286   0.03233   0.02582  -0.0466   1.0000   0.0339
 -11.000  -0.9266   0.03177   0.02525  -0.0426   1.0000   0.0345
 -10.750  -0.9250   0.03120   0.02464  -0.0386   1.0000   0.0351
 -10.500  -0.9146   0.03040   0.02375  -0.0363   0.9988   0.0359
 -10.250  -0.8882   0.02928   0.02244  -0.0371   0.9948   0.0372
 -10.000  -0.8636   0.02799   0.02088  -0.0375   0.9905   0.0386
  -9.750  -0.8370   0.02684   0.01957  -0.0382   0.9862   0.0398
  -9.500  -0.8077   0.02614   0.01884  -0.0393   0.9825   0.0410
  -9.250  -0.7809   0.02538   0.01801  -0.0397   0.9768   0.0422
  -9.000  -0.7500   0.02449   0.01698  -0.0409   0.9728   0.0437
  -8.750  -0.7226   0.02361   0.01592  -0.0412   0.9671   0.0453
  -8.500  -0.6935   0.02276   0.01498  -0.0420   0.9622   0.0468
  -8.250  -0.6611   0.02210   0.01429  -0.0433   0.9589   0.0482
  -8.000  -0.6355   0.02149   0.01363  -0.0431   0.9523   0.0497
  -7.750  -0.6050   0.02084   0.01289  -0.0440   0.9479   0.0519
  -7.500  -0.5713   0.02012   0.01205  -0.0454   0.9448   0.0541
  -7.250  -0.5446   0.01957   0.01150  -0.0454   0.9386   0.0559
  -7.000  -0.5142   0.01902   0.01093  -0.0462   0.9334   0.0582
  -6.750  -0.4808   0.01845   0.01026  -0.0474   0.9296   0.0612
  -6.500  -0.4528   0.01791   0.00968  -0.0476   0.9235   0.0641
  -6.250  -0.4242   0.01744   0.00921  -0.0480   0.9172   0.0673
  -6.000  -0.3906   0.01695   0.00865  -0.0492   0.9128   0.0714
  -5.750  -0.3649   0.01649   0.00815  -0.0489   0.9053   0.0747
  -5.500  -0.3366   0.01598   0.00765  -0.0491   0.8987   0.0786
  -5.250  -0.3062   0.01559   0.00719  -0.0497   0.8928   0.0832
  -5.000  -0.2819   0.01523   0.00681  -0.0490   0.8841   0.0873
  -4.750  -0.2518   0.01478   0.00636  -0.0495   0.8780   0.0926
  -4.500  -0.2295   0.01452   0.00606  -0.0483   0.8682   0.0975
  -4.250  -0.2009   0.01414   0.00569  -0.0485   0.8612   0.1046
  -4.000  -0.1790   0.01388   0.00545  -0.0472   0.8509   0.1132
  -3.750  -0.1531   0.01354   0.00517  -0.0468   0.8427   0.1282
  -3.500  -0.1305   0.01324   0.00498  -0.0457   0.8325   0.1533
  -3.250  -0.1065   0.01296   0.00478  -0.0449   0.8230   0.1856
  -3.000  -0.0824   0.01268   0.00454  -0.0441   0.8131   0.2134
  -2.750  -0.0604   0.01239   0.00434  -0.0429   0.8020   0.2419
  -2.500  -0.0395   0.01196   0.00414  -0.0415   0.7913   0.2978
  -2.250  -0.0210   0.01151   0.00400  -0.0396   0.7796   0.3910
  -2.000  -0.0021   0.01119   0.00388  -0.0377   0.7668   0.4543
  -1.750   0.0163   0.01085   0.00376  -0.0355   0.7538   0.5210
  -1.500   0.0355   0.01054   0.00367  -0.0335   0.7405   0.5887
  -1.250   0.0564   0.01022   0.00364  -0.0316   0.7272   0.6707
  -1.000   0.0875   0.01006   0.00372  -0.0318   0.7134   0.7482
  -0.750   0.1299   0.01011   0.00386  -0.0343   0.6997   0.8031
  -0.500   0.1714   0.01027   0.00399  -0.0367   0.6862   0.8424
  -0.250   0.2114   0.01047   0.00413  -0.0388   0.6728   0.8673
   0.000   0.2459   0.01065   0.00422  -0.0398   0.6603   0.8833
   0.250   0.2791   0.01084   0.00431  -0.0406   0.6478   0.8974
   0.500   0.3070   0.01102   0.00442  -0.0403   0.6355   0.9106
   0.750   0.3492   0.01128   0.00459  -0.0430   0.6233   0.9177
   1.000   0.3760   0.01147   0.00469  -0.0425   0.6124   0.9277
   1.250   0.4141   0.01167   0.00481  -0.0445   0.5983   0.9322
   1.500   0.4445   0.01185   0.00492  -0.0449   0.5849   0.9399
   1.750   0.4782   0.01203   0.00502  -0.0461   0.5717   0.9458
   2.000   0.5132   0.01220   0.00513  -0.0475   0.5594   0.9511
   2.250   0.5429   0.01239   0.00525  -0.0479   0.5478   0.9587
   2.500   0.5837   0.01256   0.00539  -0.0506   0.5350   0.9641
   2.750   0.6147   0.01274   0.00552  -0.0513   0.5226   0.9713
   3.000   0.6505   0.01285   0.00559  -0.0531   0.5093   0.9748
   3.250   0.6821   0.01298   0.00567  -0.0540   0.4972   0.9789
   3.500   0.7113   0.01311   0.00579  -0.0544   0.4851   0.9833
   3.750   0.7445   0.01320   0.00585  -0.0558   0.4715   0.9863
   4.000   0.7755   0.01332   0.00594  -0.0567   0.4564   0.9898
   4.250   0.8042   0.01350   0.00605  -0.0571   0.4367   0.9935
   4.500   0.8344   0.01365   0.00612  -0.0579   0.4159   0.9965
   4.750   0.8646   0.01383   0.00624  -0.0587   0.3966   0.9995
   5.000   0.8835   0.01404   0.00641  -0.0572   0.3802   1.0000
   5.250   0.8995   0.01427   0.00659  -0.0550   0.3649   1.0000
   5.500   0.9148   0.01453   0.00680  -0.0527   0.3489   1.0000
   5.750   0.9296   0.01480   0.00703  -0.0504   0.3325   1.0000
   6.000   0.9437   0.01509   0.00728  -0.0479   0.3148   1.0000
   6.250   0.9568   0.01542   0.00755  -0.0452   0.2948   1.0000
   6.500   0.9687   0.01578   0.00785  -0.0423   0.2734   1.0000
   6.750   0.9791   0.01619   0.00818  -0.0392   0.2489   1.0000
   7.000   0.9867   0.01670   0.00855  -0.0357   0.2214   1.0000
   7.250   0.9931   0.01725   0.00897  -0.0319   0.1989   1.0000
   7.500   0.9992   0.01779   0.00941  -0.0281   0.1838   1.0000
   7.750   1.0062   0.01827   0.00986  -0.0245   0.1736   1.0000
   8.250   1.0153   0.01915   0.01073  -0.0162   0.1591   1.0000
   8.500   1.0193   0.01964   0.01120  -0.0121   0.1528   1.0000
   8.750   1.0255   0.02013   0.01171  -0.0085   0.1472   1.0000
   9.000   1.0338   0.02061   0.01223  -0.0053   0.1411   1.0000
   9.250   1.0394   0.02125   0.01286  -0.0019   0.1354   1.0000
   9.500   1.0495   0.02178   0.01345   0.0007   0.1299   1.0000
   9.750   1.0581   0.02242   0.01411   0.0035   0.1242   1.0000
  10.000   1.0653   0.02316   0.01485   0.0062   0.1194   1.0000
  10.250   1.0756   0.02383   0.01559   0.0085   0.1148   1.0000
  10.500   1.0843   0.02461   0.01640   0.0108   0.1107   1.0000
  10.750   1.0912   0.02554   0.01734   0.0131   0.1075   1.0000
  11.000   1.1007   0.02640   0.01826   0.0151   0.1043   1.0000
  11.250   1.1099   0.02731   0.01924   0.0170   0.1015   1.0000
  11.500   1.1182   0.02832   0.02029   0.0188   0.0986   1.0000
  11.750   1.1246   0.02948   0.02146   0.0206   0.0956   1.0000
  12.000   1.1325   0.03061   0.02265   0.0222   0.0927   1.0000
  12.250   1.1416   0.03171   0.02384   0.0236   0.0899   1.0000
  12.500   1.1492   0.03295   0.02513   0.0250   0.0868   1.0000
  12.750   1.1552   0.03435   0.02657   0.0263   0.0847   1.0000
  13.000   1.1592   0.03597   0.02819   0.0276   0.0823   1.0000
  13.250   1.1682   0.03725   0.02960   0.0285   0.0801   1.0000
  13.500   1.1760   0.03867   0.03114   0.0294   0.0778   1.0000
  13.750   1.1819   0.04027   0.03282   0.0302   0.0754   1.0000
  14.000   1.1860   0.04210   0.03469   0.0309   0.0733   1.0000
  14.250   1.1878   0.04417   0.03678   0.0316   0.0713   1.0000
  14.500   1.1955   0.04579   0.03856   0.0320   0.0690   1.0000
  14.750   1.2012   0.04765   0.04055   0.0323   0.0665   1.0000
  15.000   1.2051   0.04975   0.04275   0.0325   0.0643   1.0000
  15.250   1.2065   0.05216   0.04521   0.0325   0.0622   1.0000
  15.500   1.2084   0.05457   0.04771   0.0325   0.0603   1.0000
  15.750   1.2128   0.05677   0.05005   0.0325   0.0583   1.0000
  16.000   1.2153   0.05929   0.05270   0.0322   0.0556   1.0000
  16.250   1.2145   0.06224   0.05573   0.0317   0.0533   1.0000
  16.500   1.2135   0.06528   0.05885   0.0311   0.0511   1.0000
  16.750   1.2145   0.06811   0.06184   0.0305   0.0485   1.0000
  17.000   1.2121   0.07150   0.06533   0.0296   0.0458   1.0000
  17.250   1.2080   0.07520   0.06913   0.0286   0.0427   1.0000
  17.500   1.2037   0.07897   0.07300   0.0274   0.0395   1.0000
  17.750   1.1964   0.08325   0.07738   0.0260   0.0367   1.0000
  18.000   1.1890   0.08765   0.08189   0.0244   0.0339   1.0000
  18.250   1.1773   0.09285   0.08716   0.0224   0.0312   1.0000
  18.500   1.1658   0.09806   0.09248   0.0203   0.0293   1.0000
  18.750   1.1523   0.10375   0.09827   0.0179   0.0281   1.0000
  19.000   1.1367   0.10994   0.10457   0.0152   0.0268   1.0000
  19.250   1.1203   0.11639   0.11115   0.0122   0.0258   1.0000
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