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Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 2 (fg2-il)
Reynolds number: 50,000
Max Cl/Cd: 33.16 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg2-il-50000.txt
Download as CSV file: xf-fg2-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 2                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4217   0.10571   0.09898  -0.0158   1.0000   0.1762
  -8.250  -0.4114   0.10156   0.09484  -0.0144   1.0000   0.1866
  -8.000  -0.4299   0.10068   0.09413  -0.0153   1.0000   0.1917
  -7.750  -0.4203   0.09669   0.09017  -0.0136   1.0000   0.2047
  -7.500  -0.4175   0.09337   0.08693  -0.0124   1.0000   0.2140
  -7.250  -0.4383   0.09241   0.08613  -0.0139   1.0000   0.2218
  -7.000  -0.4323   0.08890   0.08269  -0.0121   1.0000   0.2359
  -6.750  -0.4309   0.08586   0.07972  -0.0108   1.0000   0.2506
  -6.500  -0.4350   0.08337   0.07732  -0.0103   1.0000   0.2663
  -6.250  -0.4217   0.07930   0.07330  -0.0060   1.0000   0.2886
  -6.000  -0.4294   0.07739   0.07149  -0.0053   1.0000   0.3105
  -5.750  -0.4263   0.07449   0.06868  -0.0016   1.0000   0.3399
  -5.500  -0.4163   0.07132   0.06559   0.0043   1.0000   0.3801
  -5.250  -0.0174   0.04781   0.04072  -0.0223   1.0000   1.0000
  -5.000  -0.0077   0.04574   0.03871  -0.0229   1.0000   1.0000
  -4.750   0.0021   0.04373   0.03674  -0.0233   1.0000   1.0000
  -4.500  -0.0317   0.04449   0.03771  -0.0130   1.0000   0.9760
  -4.250  -0.0914   0.04603   0.03958   0.0017   1.0000   0.9246
  -4.000  -0.1466   0.04692   0.04075   0.0133   1.0000   0.8766
  -3.750  -0.1973   0.04685   0.04095   0.0220   1.0000   0.8240
  -3.500  -0.2454   0.04644   0.04083   0.0302   1.0000   0.7903
  -3.250  -0.2934   0.04568   0.04036   0.0384   1.0000   0.7642
  -3.000  -0.3381   0.04473   0.03966   0.0465   1.0000   0.7498
  -2.750  -0.2793   0.03827   0.03105  -0.0099   1.0000   0.3110
  -2.500  -0.2371   0.03545   0.02713  -0.0127   1.0000   0.2208
  -2.250  -0.2111   0.03347   0.02457  -0.0119   1.0000   0.1900
  -2.000  -0.1882   0.03186   0.02253  -0.0107   1.0000   0.1731
  -1.750  -0.1663   0.03088   0.02099  -0.0091   1.0000   0.1619
  -1.500  -0.1477   0.02976   0.01968  -0.0078   1.0000   0.1601
  -1.250  -0.1293   0.02888   0.01860  -0.0065   1.0000   0.1579
  -1.000  -0.1102   0.02821   0.01765  -0.0055   1.0000   0.1535
  -0.750  -0.0920   0.02789   0.01702  -0.0044   1.0000   0.1500
  -0.500  -0.0749   0.02776   0.01669  -0.0034   1.0000   0.1483
  -0.250  -0.0313   0.02752   0.01623  -0.0072   0.9929   0.1481
   0.000   0.0431   0.02704   0.01569  -0.0164   0.9745   0.1580
   0.250   0.1055   0.02667   0.01528  -0.0233   0.9536   0.1697
   0.500   0.1715   0.02612   0.01488  -0.0308   0.9344   0.2015
   0.750   0.2861   0.02379   0.01425  -0.0471   0.9182   1.0000
   1.000   0.3464   0.02383   0.01392  -0.0531   0.8949   1.0000
   1.250   0.4058   0.02367   0.01354  -0.0587   0.8719   1.0000
   1.500   0.4707   0.02326   0.01301  -0.0650   0.8503   1.0000
   1.750   0.5205   0.02305   0.01272  -0.0684   0.8258   1.0000
   2.000   0.5752   0.02268   0.01228  -0.0724   0.8034   1.0000
   2.250   0.6129   0.02275   0.01232  -0.0736   0.7788   1.0000
   2.500   0.6490   0.02291   0.01242  -0.0744   0.7559   1.0000
   2.750   0.6832   0.02318   0.01266  -0.0750   0.7348   1.0000
   3.000   0.7141   0.02362   0.01305  -0.0751   0.7153   1.0000
   3.250   0.7380   0.02432   0.01379  -0.0743   0.6963   1.0000
   3.500   0.7629   0.02503   0.01452  -0.0736   0.6794   1.0000
   3.750   0.7871   0.02580   0.01531  -0.0728   0.6634   1.0000
   4.000   0.8110   0.02652   0.01605  -0.0718   0.6471   1.0000
   4.250   0.8370   0.02698   0.01653  -0.0706   0.6285   1.0000
   4.500   0.8546   0.02770   0.01730  -0.0684   0.6081   1.0000
   4.750   0.8774   0.02821   0.01783  -0.0667   0.5888   1.0000
   5.000   0.9007   0.02881   0.01848  -0.0653   0.5717   1.0000
   5.250   0.9225   0.02952   0.01929  -0.0638   0.5549   1.0000
   5.500   0.9393   0.03045   0.02037  -0.0617   0.5375   1.0000
   5.750   0.9574   0.03130   0.02135  -0.0597   0.5193   1.0000
   6.000   0.9785   0.03200   0.02215  -0.0580   0.5006   1.0000
   6.250   1.0028   0.03260   0.02281  -0.0565   0.4817   1.0000
   6.500   1.0152   0.03384   0.02432  -0.0538   0.4614   1.0000
   6.750   1.0371   0.03455   0.02511  -0.0520   0.4406   1.0000
   7.000   1.0541   0.03563   0.02634  -0.0498   0.4205   1.0000
   7.250   1.0689   0.03700   0.02790  -0.0475   0.4020   1.0000
   7.500   1.0847   0.03856   0.02966  -0.0455   0.3863   1.0000
   7.750   1.1058   0.03935   0.03062  -0.0437   0.3689   1.0000
   8.000   1.1244   0.03952   0.03088  -0.0414   0.3474   1.0000
   8.250   1.1465   0.03796   0.02924  -0.0388   0.3170   1.0000
   8.500   1.1599   0.03629   0.02750  -0.0351   0.2842   1.0000
   8.750   1.1651   0.03514   0.02632  -0.0306   0.2520   1.0000
   9.000   1.1589   0.03505   0.02633  -0.0248   0.2142   1.0000
   9.250   1.1450   0.03639   0.02711  -0.0185   0.1690   1.0000
   9.500   1.1357   0.03939   0.02976  -0.0137   0.1336   1.0000
   9.750   1.1405   0.04224   0.03231  -0.0107   0.1137   1.0000
  10.000   1.1521   0.04500   0.03521  -0.0085   0.1019   1.0000
  10.250   1.1637   0.04799   0.03843  -0.0065   0.0942   1.0000
  10.500   1.1787   0.05058   0.04089  -0.0053   0.0870   1.0000
  10.750   1.1759   0.05355   0.04435  -0.0020   0.0839   1.0000
  11.000   1.1745   0.05669   0.04782   0.0007   0.0814   1.0000
  11.250   1.1717   0.06003   0.05143   0.0031   0.0795   1.0000
  11.500   1.1641   0.06363   0.05530   0.0053   0.0788   1.0000
  11.750   1.1507   0.06757   0.05951   0.0071   0.0785   1.0000
  12.000   1.1284   0.07216   0.06438   0.0081   0.0788   1.0000
  12.250   1.0965   0.07797   0.07049   0.0071   0.0801   1.0000
  12.500   1.0620   0.08517   0.07790   0.0039   0.0816   1.0000
  12.750   1.0296   0.09351   0.08637  -0.0006   0.0837   1.0000
  13.000   1.0022   0.10229   0.09521  -0.0054   0.0855   1.0000
  13.250   0.9821   0.11068   0.10361  -0.0094   0.0868   1.0000
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