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GOE 614 AIRFOIL (goe614-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 614 AIRFOIL (goe614-il)
Reynolds number: 50,000
Max Cl/Cd: 16.1 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe614-il-50000-n5.txt
Download as CSV file: xf-goe614-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 614 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1330   0.11095   0.10400  -0.0795   0.9367   0.0772
  -9.750  -0.1294   0.10630   0.09935  -0.0827   0.9285   0.0766
  -9.500  -0.1264   0.10104   0.09409  -0.0868   0.9217   0.0760
  -9.250  -0.1304   0.09597   0.08904  -0.0897   0.9121   0.0755
  -9.000  -0.1381   0.08964   0.08272  -0.0940   0.9043   0.0749
  -8.750  -0.2111   0.07454   0.06756  -0.1030   0.8919   0.0731
  -8.500  -0.2547   0.06747   0.06038  -0.1064   0.8769   0.0725
  -8.250  -0.2892   0.06116   0.05379  -0.1085   0.8626   0.0722
  -8.000  -0.2960   0.05514   0.04731  -0.1119   0.8548   0.0725
  -7.750  -0.3063   0.05222   0.04406  -0.1101   0.8414   0.0728
  -7.500  -0.2840   0.04907   0.04059  -0.1122   0.8363   0.0738
  -7.250  -0.2813   0.04795   0.03939  -0.1096   0.8235   0.0747
  -7.000  -0.2525   0.04589   0.03712  -0.1113   0.8186   0.0770
  -6.750  -0.2483   0.04466   0.03569  -0.1088   0.8062   0.0788
  -6.500  -0.2196   0.04242   0.03305  -0.1101   0.8010   0.0817
  -6.250  -0.2098   0.04178   0.03239  -0.1079   0.7896   0.0837
  -6.000  -0.1811   0.04033   0.03076  -0.1085   0.7836   0.0871
  -5.750  -0.1641   0.03924   0.02941  -0.1072   0.7745   0.0905
  -5.500  -0.1410   0.03821   0.02833  -0.1068   0.7666   0.0948
  -5.250  -0.1055   0.03669   0.02660  -0.1082   0.7624   0.1031
  -5.000  -0.1001   0.03637   0.02629  -0.1050   0.7501   0.1095
  -4.750  -0.0668   0.03509   0.02493  -0.1061   0.7451   0.1279
  -4.500  -0.0559   0.03491   0.02485  -0.1038   0.7343   0.1424
  -4.250  -0.0253   0.03449   0.02446  -0.1042   0.7281   0.1665
  -4.000  -0.0004   0.03443   0.02430  -0.1038   0.7208   0.1906
  -3.750   0.0179   0.03455   0.02434  -0.1024   0.7116   0.2095
  -3.500   0.0554   0.03416   0.02382  -0.1037   0.7073   0.2316
  -3.250   0.0624   0.03453   0.02407  -0.1007   0.6960   0.2443
  -3.000   0.0947   0.03430   0.02375  -0.1012   0.6908   0.2650
  -2.750   0.1153   0.03438   0.02373  -0.1001   0.6831   0.2819
  -2.500   0.1342   0.03451   0.02389  -0.0987   0.6750   0.2963
  -2.250   0.1721   0.03400   0.02325  -0.0999   0.6710   0.3138
  -2.000   0.1784   0.03450   0.02365  -0.0969   0.6609   0.3238
  -1.750   0.2078   0.03424   0.02329  -0.0969   0.6553   0.3374
  -1.500   0.2482   0.03369   0.02261  -0.0984   0.6518   0.3532
  -1.250   0.2477   0.03460   0.02345  -0.0946   0.6409   0.3628
  -1.000   0.2804   0.03436   0.02310  -0.0951   0.6362   0.3806
  -0.750   0.3205   0.03390   0.02259  -0.0966   0.6331   0.4042
  -0.500   0.3125   0.03524   0.02400  -0.0919   0.6220   0.4150
  -0.250   0.3452   0.03500   0.02369  -0.0923   0.6176   0.4392
   0.000   0.3864   0.03446   0.02307  -0.0939   0.6147   0.4642
   0.250   0.3741   0.03619   0.02489  -0.0890   0.6035   0.4738
   0.500   0.4058   0.03600   0.02467  -0.0894   0.5994   0.4979
   0.750   0.4458   0.03545   0.02408  -0.0907   0.5966   0.5270
   1.250   0.4592   0.03741   0.02621  -0.0857   0.5813   0.5746
   1.750   0.4767   0.03935   0.02846  -0.0816   0.5678   0.6469
   2.000   0.5029   0.03916   0.02857  -0.0809   0.5634   0.7331
   2.250   0.5662   0.03830   0.02781  -0.0864   0.5608   1.0000
   2.500   0.6100   0.03789   0.02708  -0.0883   0.5586   1.0000
   2.750   0.5648   0.04213   0.03140  -0.0814   0.5450   1.0000
   3.000   0.6000   0.04196   0.03100  -0.0821   0.5422   1.0000
   3.250   0.6408   0.04151   0.03031  -0.0832   0.5403   1.0000
   3.750   0.6290   0.04621   0.03492  -0.0777   0.5234   1.0000
   4.250   0.6236   0.05114   0.03977  -0.0738   0.5066   1.0000
   4.500   0.6068   0.05510   0.04373  -0.0716   0.4958   1.0000
   4.750   0.6238   0.05608   0.04462  -0.0709   0.4902   1.0000
   5.000   0.6547   0.05581   0.04422  -0.0706   0.4874   1.0000
   5.250   0.6898   0.05518   0.04344  -0.0705   0.4855   1.0000
   6.250   0.6865   0.06577   0.05396  -0.0655   0.4515   1.0000
   6.500   0.7177   0.06538   0.05348  -0.0651   0.4493   1.0000
   7.000   0.7143   0.07118   0.05928  -0.0633   0.4326   1.0000
   7.250   0.7437   0.07098   0.05900  -0.0628   0.4304   1.0000
   7.750   0.7368   0.07747   0.06553  -0.0614   0.4141   1.0000
   8.250   0.7293   0.08426   0.07235  -0.0603   0.3984   1.0000
   8.500   0.7553   0.08446   0.07251  -0.0599   0.3961   1.0000
   9.000   0.7440   0.09201   0.08012  -0.0594   0.3810   1.0000
   9.250   0.7661   0.09275   0.08083  -0.0590   0.3788   1.0000
   9.500   0.7362   0.09973   0.08790  -0.0595   0.3693   1.0000
   9.750   0.7469   0.10187   0.09005  -0.0594   0.3655   1.0000
  10.000   0.7649   0.10311   0.09128  -0.0591   0.3630   1.0000
  10.250   0.7852   0.10408   0.09223  -0.0588   0.3608   1.0000
  10.500   0.7540   0.11126   0.09951  -0.0598   0.3517   1.0000
  10.750   0.7662   0.11324   0.10151  -0.0598   0.3485   1.0000
  11.000   0.7853   0.11437   0.10264  -0.0595   0.3462   1.0000
  11.250   0.7837   0.11815   0.10646  -0.0600   0.3423   1.0000
  11.500   0.7727   0.12301   0.11139  -0.0609   0.3372   1.0000
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