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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
Reynolds number: 500,000
Max Cl/Cd: 89.81 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe199-il-500000.txt
Download as CSV file: xf-goe199-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 199 (L.F.G. 5406) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3420   0.09922   0.09705  -0.0160   1.0000   0.0171
  -8.000  -0.3374   0.09634   0.09421  -0.0185   1.0000   0.0173
  -7.750  -0.3348   0.09356   0.09146  -0.0214   1.0000   0.0173
  -7.500  -0.2355   0.07476   0.07284  -0.0323   0.9905   0.0177
  -7.250  -0.2217   0.07054   0.06862  -0.0347   0.9825   0.0179
  -7.000  -0.3000   0.08193   0.07988  -0.0347   0.9953   0.0176
  -6.750  -0.2822   0.07792   0.07586  -0.0360   0.9906   0.0178
  -6.500  -0.2575   0.07402   0.07194  -0.0408   0.9837   0.0182
  -6.250  -0.2317   0.07020   0.06809  -0.0462   0.9730   0.0187
  -6.000  -0.2063   0.06651   0.06434  -0.0511   0.9599   0.0196
  -5.750  -0.1719   0.06250   0.06021  -0.0586   0.9447   0.0210
  -5.500  -0.1356   0.05809   0.05560  -0.0658   0.9308   0.0213
  -5.250  -0.1129   0.05364   0.05102  -0.0685   0.9192   0.0214
  -5.000  -0.1002   0.05064   0.04799  -0.0681   0.9088   0.0217
  -4.750  -0.0810   0.04810   0.04539  -0.0688   0.8984   0.0220
  -4.500  -0.0578   0.04565   0.04284  -0.0702   0.8892   0.0227
  -4.250  -0.0312   0.04300   0.04007  -0.0720   0.8805   0.0238
  -4.000   0.0134   0.03987   0.03659  -0.0755   0.8723   0.0258
  -3.750   0.0453   0.03700   0.03342  -0.0768   0.8648   0.0260
  -3.250   0.0897   0.03135   0.02764  -0.0786   0.8492   0.0271
  -3.000   0.1164   0.02957   0.02574  -0.0793   0.8390   0.0280
  -2.750   0.1448   0.02767   0.02364  -0.0796   0.8260   0.0294
  -2.500   0.1811   0.02656   0.02204  -0.0791   0.8124   0.0318
  -2.250   0.2078   0.02312   0.01835  -0.0799   0.8006   0.0325
  -2.000   0.2342   0.02173   0.01689  -0.0804   0.7896   0.0334
  -1.750   0.2619   0.02061   0.01566  -0.0807   0.7796   0.0347
  -1.500   0.2912   0.01950   0.01432  -0.0807   0.7707   0.0371
  -1.250   0.3225   0.01804   0.01247  -0.0807   0.7610   0.0404
  -1.000   0.3500   0.01693   0.01133  -0.0811   0.7507   0.0419
  -0.750   0.3782   0.01621   0.01047  -0.0812   0.7396   0.0445
  -0.500   0.4080   0.01556   0.00950  -0.0810   0.7274   0.0504
  -0.250   0.4358   0.01468   0.00863  -0.0814   0.7147   0.0533
   0.000   0.4648   0.01574   0.00950  -0.0810   0.7004   0.0603
   0.250   0.4925   0.01357   0.00729  -0.0815   0.6855   0.0660
   0.500   0.5208   0.01311   0.00668  -0.0816   0.6676   0.0766
   0.750   0.5488   0.01268   0.00614  -0.0817   0.6464   0.0897
   1.250   0.6074   0.01155   0.00448  -0.0805   0.5935   0.0496
   1.500   0.6348   0.01118   0.00399  -0.0803   0.5645   0.0474
   1.750   0.6621   0.01098   0.00366  -0.0802   0.5382   0.0466
   2.250   0.7171   0.01075   0.00322  -0.0800   0.4915   0.0436
   2.500   0.7446   0.01077   0.00314  -0.0800   0.4677   0.0436
   2.750   0.7722   0.01083   0.00310  -0.0800   0.4402   0.0445
   3.000   0.7993   0.01099   0.00312  -0.0800   0.4073   0.0459
   3.250   0.8261   0.01124   0.00319  -0.0800   0.3705   0.0477
   3.500   0.8526   0.01153   0.00331  -0.0799   0.3376   0.0526
   3.750   0.8793   0.01181   0.00349  -0.0798   0.3119   0.0669
   4.000   0.9042   0.01040   0.00377  -0.0798   0.2923   1.0000
   4.250   0.9308   0.01072   0.00396  -0.0798   0.2759   1.0000
   4.500   0.9575   0.01102   0.00417  -0.0797   0.2629   1.0000
   4.750   0.9841   0.01131   0.00439  -0.0796   0.2530   1.0000
   5.000   1.0106   0.01161   0.00463  -0.0795   0.2451   1.0000
   5.250   1.0372   0.01187   0.00488  -0.0794   0.2387   1.0000
   5.500   1.0636   0.01214   0.00511  -0.0794   0.2320   1.0000
   5.750   1.0897   0.01246   0.00541  -0.0792   0.2266   1.0000
   6.000   1.1164   0.01266   0.00564  -0.0792   0.2218   1.0000
   6.250   1.1423   0.01296   0.00591  -0.0790   0.2157   1.0000
   6.500   1.1685   0.01321   0.00618  -0.0789   0.2103   1.0000
   6.750   1.1947   0.01343   0.00643  -0.0788   0.2048   1.0000
   7.250   1.2465   0.01394   0.00697  -0.0785   0.1931   1.0000
   7.500   1.2718   0.01423   0.00726  -0.0783   0.1862   1.0000
   7.750   1.2977   0.01445   0.00752  -0.0782   0.1764   1.0000
   8.000   1.3226   0.01478   0.00780  -0.0780   0.1604   1.0000
   8.250   1.3366   0.01649   0.00891  -0.0764   0.0654   1.0000
   8.500   1.3528   0.01791   0.01013  -0.0749   0.0344   1.0000
   8.750   1.3728   0.01879   0.01109  -0.0738   0.0291   1.0000
   9.000   1.3929   0.01957   0.01195  -0.0728   0.0262   1.0000
   9.250   1.4078   0.02086   0.01335  -0.0711   0.0235   1.0000
   9.500   1.4265   0.02163   0.01422  -0.0698   0.0223   1.0000
   9.750   1.4439   0.02246   0.01514  -0.0685   0.0209   1.0000
  10.000   1.4595   0.02335   0.01610  -0.0669   0.0196   1.0000
  10.250   1.4694   0.02459   0.01742  -0.0645   0.0185   1.0000
  10.500   1.4662   0.02653   0.01950  -0.0602   0.0176   1.0000
  10.750   1.4744   0.02749   0.02056  -0.0574   0.0172   1.0000
  11.000   1.4794   0.02875   0.02193  -0.0546   0.0167   1.0000
  11.250   1.4832   0.03024   0.02354  -0.0520   0.0162   1.0000
  11.500   1.4862   0.03193   0.02534  -0.0496   0.0157   1.0000
  11.750   1.4889   0.03379   0.02729  -0.0477   0.0152   1.0000
  12.000   1.4915   0.03577   0.02937  -0.0460   0.0148   1.0000
  12.250   1.4928   0.03801   0.03168  -0.0446   0.0144   1.0000
  12.500   1.4902   0.04074   0.03450  -0.0433   0.0140   1.0000
  12.750   1.4813   0.04428   0.03814  -0.0419   0.0136   1.0000
  13.000   1.4724   0.04796   0.04194  -0.0405   0.0133   1.0000
  13.250   1.4746   0.05056   0.04468  -0.0401   0.0131   1.0000
  13.500   1.4743   0.05351   0.04776  -0.0397   0.0128   1.0000
  13.750   1.4727   0.05667   0.05105  -0.0393   0.0126   1.0000
  14.000   1.4704   0.05998   0.05448  -0.0391   0.0124   1.0000
  14.250   1.4677   0.06343   0.05806  -0.0391   0.0122   1.0000
  14.500   1.4644   0.06701   0.06175  -0.0391   0.0120   1.0000
  14.750   1.4610   0.07071   0.06558  -0.0394   0.0118   1.0000
  15.000   1.4574   0.07456   0.06955  -0.0399   0.0116   1.0000
  15.250   1.4535   0.07852   0.07364  -0.0405   0.0114   1.0000
  15.500   1.4491   0.08262   0.07786  -0.0412   0.0113   1.0000
  15.750   1.4437   0.08698   0.08234  -0.0423   0.0111   1.0000
  16.000   1.4380   0.09151   0.08699  -0.0435   0.0110   1.0000
  16.250   1.4318   0.09620   0.09181  -0.0450   0.0108   1.0000
  16.500   1.4251   0.10104   0.09676  -0.0467   0.0107   1.0000
  16.750   1.4185   0.10592   0.10175  -0.0486   0.0106   1.0000
  17.000   1.4118   0.11084   0.10677  -0.0505   0.0104   1.0000
  17.250   1.4043   0.11594   0.11198  -0.0524   0.0103   1.0000
  17.500   1.3943   0.12147   0.11763  -0.0545   0.0102   1.0000
  17.750   1.3812   0.12786   0.12418  -0.0573   0.0101   1.0000
  18.000   1.3665   0.13494   0.13144  -0.0609   0.0100   1.0000
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