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GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 199 (L.F.G. 5406) AIRFOIL (goe199-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.17 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe199-il-1000000.txt
Download as CSV file: xf-goe199-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3823   0.11321   0.11162  -0.0086   1.0000   0.0113
  -9.250  -0.3773   0.10974   0.10816  -0.0108   1.0000   0.0113
  -9.000  -0.3719   0.10631   0.10475  -0.0128   1.0000   0.0113
  -8.750  -0.3658   0.10249   0.10094  -0.0129   1.0000   0.0115
  -8.500  -0.3587   0.09961   0.09807  -0.0139   1.0000   0.0116
  -8.250  -0.3518   0.09682   0.09529  -0.0152   1.0000   0.0117
  -8.000  -0.3455   0.09404   0.09253  -0.0166   1.0000   0.0119
  -7.750  -0.3405   0.09133   0.08984  -0.0179   1.0000   0.0121
  -7.250  -0.3089   0.08408   0.08260  -0.0270   0.9763   0.0135
  -7.000  -0.2883   0.07943   0.07788  -0.0345   0.9514   0.0141
  -6.750  -0.2708   0.07504   0.07340  -0.0405   0.9276   0.0141
  -6.500  -0.2516   0.07075   0.06900  -0.0455   0.9090   0.0142
  -6.250  -0.2406   0.06679   0.06497  -0.0462   0.8939   0.0143
  -6.000  -0.2240   0.06405   0.06216  -0.0477   0.8807   0.0145
  -5.750  -0.2035   0.06125   0.05930  -0.0502   0.8695   0.0148
  -5.500  -0.1806   0.05833   0.05630  -0.0531   0.8595   0.0152
  -5.250  -0.1554   0.05524   0.05311  -0.0564   0.8500   0.0163
  -5.000  -0.1096   0.04973   0.04738  -0.0642   0.8418   0.0174
  -4.750  -0.0808   0.04597   0.04346  -0.0670   0.8340   0.0175
  -4.500  -0.0592   0.04181   0.03920  -0.0691   0.8267   0.0177
  -4.250  -0.0359   0.03981   0.03713  -0.0701   0.8193   0.0180
  -4.000  -0.0100   0.03786   0.03510  -0.0714   0.8117   0.0185
  -3.750   0.0183   0.03566   0.03275  -0.0727   0.8014   0.0196
  -3.500   0.0591   0.03241   0.02918  -0.0744   0.7891   0.0212
  -3.250   0.0892   0.02969   0.02623  -0.0752   0.7754   0.0213
  -3.000   0.1162   0.02570   0.02201  -0.0766   0.7645   0.0217
  -2.750   0.1426   0.02440   0.02060  -0.0772   0.7550   0.0221
  -2.500   0.1706   0.02305   0.01915  -0.0778   0.7464   0.0226
  -2.250   0.1995   0.02165   0.01759  -0.0782   0.7379   0.0235
  -2.000   0.2325   0.02047   0.01612  -0.0779   0.7284   0.0258
  -1.750   0.2625   0.01921   0.01463  -0.0780   0.7184   0.0259
  -1.500   0.2921   0.01785   0.01299  -0.0782   0.7085   0.0260
   1.750   0.3095   0.03477   0.03145  -0.0557   0.5247   0.0314
   2.000   0.6893   0.00982   0.00292  -0.0801   0.4109   0.0347
   2.250   0.7169   0.00986   0.00280  -0.0801   0.3787   0.0335
   2.500   0.7444   0.01000   0.00278  -0.0802   0.3473   0.0329
   2.750   0.7720   0.01009   0.00276  -0.0803   0.3209   0.0330
   3.000   0.7996   0.01020   0.00276  -0.0804   0.2995   0.0341
   3.250   0.8272   0.01033   0.00281  -0.0804   0.2793   0.0354
   3.500   0.8547   0.01050   0.00289  -0.0805   0.2617   0.0366
   3.750   0.8823   0.01065   0.00298  -0.0806   0.2485   0.0378
   4.000   0.9099   0.01079   0.00309  -0.0807   0.2383   0.0398
   4.250   0.9374   0.01095   0.00321  -0.0807   0.2294   0.0467
   4.500   0.9624   0.00942   0.00351  -0.0807   0.2234   1.0000
   4.750   0.9897   0.00964   0.00366  -0.0808   0.2156   1.0000
   5.000   1.0171   0.00982   0.00382  -0.0808   0.2104   1.0000
   5.250   1.0444   0.01000   0.00397  -0.0809   0.2055   1.0000
   5.500   1.0714   0.01024   0.00417  -0.0809   0.1995   1.0000
   5.750   1.0987   0.01039   0.00433  -0.0809   0.1951   1.0000
   6.000   1.1257   0.01059   0.00450  -0.0809   0.1892   1.0000
   6.250   1.1524   0.01083   0.00471  -0.0809   0.1838   1.0000
   6.500   1.1796   0.01097   0.00488  -0.0810   0.1801   1.0000
   6.750   1.2063   0.01118   0.00509  -0.0809   0.1749   1.0000
   7.000   1.2327   0.01142   0.00531  -0.0809   0.1686   1.0000
   7.250   1.2591   0.01164   0.00552  -0.0809   0.1607   1.0000
   7.500   1.2850   0.01193   0.00577  -0.0808   0.1492   1.0000
   7.750   1.3024   0.01338   0.00673  -0.0796   0.0715   1.0000
   8.000   1.3216   0.01457   0.00767  -0.0786   0.0305   1.0000
   8.250   1.3451   0.01510   0.00820  -0.0781   0.0257   1.0000
   8.500   1.3685   0.01562   0.00876  -0.0776   0.0223   1.0000
   8.750   1.3920   0.01609   0.00926  -0.0771   0.0202   1.0000
   9.000   1.4134   0.01682   0.01003  -0.0763   0.0176   1.0000
   9.250   1.4368   0.01722   0.01046  -0.0758   0.0166   1.0000
   9.500   1.4592   0.01771   0.01099  -0.0752   0.0154   1.0000
   9.750   1.4799   0.01838   0.01169  -0.0743   0.0142   1.0000
  10.000   1.4978   0.01928   0.01270  -0.0730   0.0132   1.0000
  10.250   1.5185   0.01983   0.01330  -0.0721   0.0127   1.0000
  10.500   1.5378   0.02046   0.01399  -0.0710   0.0121   1.0000
  10.750   1.5562   0.02111   0.01469  -0.0699   0.0114   1.0000
  11.000   1.5728   0.02184   0.01546  -0.0684   0.0108   1.0000
  11.250   1.5806   0.02314   0.01686  -0.0657   0.0102   1.0000
  11.500   1.5880   0.02430   0.01814  -0.0629   0.0098   1.0000
  11.750   1.5964   0.02514   0.01906  -0.0601   0.0096   1.0000
  12.000   1.6031   0.02616   0.02017  -0.0573   0.0094   1.0000
  12.250   1.6090   0.02737   0.02146  -0.0548   0.0091   1.0000
  12.500   1.6143   0.02873   0.02292  -0.0525   0.0089   1.0000
  12.750   1.6191   0.03025   0.02453  -0.0505   0.0086   1.0000
  13.000   1.6232   0.03196   0.02632  -0.0488   0.0084   1.0000
  13.250   1.6263   0.03386   0.02831  -0.0472   0.0082   1.0000
  13.500   1.6273   0.03610   0.03065  -0.0459   0.0080   1.0000
  13.750   1.6249   0.03882   0.03346  -0.0448   0.0078   1.0000
  14.000   1.6180   0.04220   0.03696  -0.0438   0.0077   1.0000
  14.250   1.6052   0.04647   0.04138  -0.0432   0.0075   1.0000
  14.500   1.5879   0.05153   0.04659  -0.0431   0.0074   1.0000
  14.750   1.5687   0.05714   0.05235  -0.0435   0.0073   1.0000
  15.000   1.5665   0.06077   0.05610  -0.0441   0.0072   1.0000
  15.250   1.5620   0.06489   0.06033  -0.0450   0.0071   1.0000
  15.500   1.5553   0.06949   0.06504  -0.0462   0.0071   1.0000
  15.750   1.5465   0.07446   0.07013  -0.0476   0.0070   1.0000
  16.000   1.5368   0.07967   0.07546  -0.0491   0.0069   1.0000
  16.250   1.5258   0.08516   0.08106  -0.0508   0.0069   1.0000
  16.500   1.5147   0.09073   0.08674  -0.0526   0.0068   1.0000
  16.750   1.5030   0.09641   0.09254  -0.0545   0.0067   1.0000
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