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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 100,000
Max Cl/Cd: 47.32 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg4-il-100000-n5.txt
Download as CSV file: xf-fg4-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 4                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2725   0.09593   0.09116  -0.0420   0.9806   0.0656
  -8.000  -0.2856   0.09229   0.08748  -0.0511   0.9673   0.0665
  -7.750  -0.2782   0.08779   0.08295  -0.0547   0.9583   0.0669
  -7.500  -0.2573   0.08424   0.07947  -0.0535   0.9551   0.0677
  -7.250  -0.2434   0.08118   0.07644  -0.0534   0.9479   0.0689
  -7.000  -0.2256   0.07759   0.07282  -0.0562   0.9416   0.0704
  -6.750  -0.2137   0.07412   0.06932  -0.0584   0.9319   0.0723
  -6.500  -0.2040   0.07024   0.06507  -0.0652   0.9191   0.0770
  -6.250  -0.1907   0.06595   0.06067  -0.0668   0.9114   0.0780
  -6.000  -0.1705   0.06244   0.05726  -0.0670   0.9055   0.0792
  -5.750  -0.1453   0.05930   0.05411  -0.0686   0.9015   0.0813
  -5.500  -0.1315   0.05679   0.05154  -0.0682   0.8911   0.0838
  -5.000  -0.0961   0.05097   0.04536  -0.0694   0.8736   0.0935
  -4.750  -0.0682   0.04840   0.04273  -0.0707   0.8687   0.0980
  -4.250  -0.0406   0.04412   0.03816  -0.0678   0.8453   0.1102
  -3.750  -0.0049   0.03757   0.03058  -0.0627   0.8219   0.0682
  -3.500   0.0168   0.03487   0.02753  -0.0608   0.8119   0.0559
  -3.250   0.0380   0.03296   0.02542  -0.0593   0.8013   0.0539
  -3.000   0.0553   0.03116   0.02290  -0.0557   0.7884   0.0500
  -2.750   0.0832   0.02950   0.02110  -0.0555   0.7791   0.0496
  -2.500   0.1102   0.02806   0.01933  -0.0548   0.7683   0.0503
  -2.250   0.1384   0.02671   0.01787  -0.0546   0.7566   0.0510
  -2.000   0.1770   0.02529   0.01615  -0.0561   0.7468   0.0511
  -1.750   0.2107   0.02426   0.01472  -0.0563   0.7333   0.0503
  -1.500   0.2465   0.02329   0.01350  -0.0574   0.7199   0.0500
  -1.000   0.3276   0.02143   0.01129  -0.0617   0.6946   0.0503
  -0.750   0.3602   0.02080   0.01059  -0.0624   0.6813   0.0507
  -0.500   0.3972   0.02022   0.00996  -0.0641   0.6688   0.0515
  -0.250   0.4301   0.01982   0.00953  -0.0650   0.6561   0.0539
   0.000   0.4556   0.01952   0.00919  -0.0643   0.6424   0.0557
   0.250   0.4808   0.01924   0.00884  -0.0634   0.6266   0.0567
   0.500   0.5040   0.01903   0.00852  -0.0621   0.6099   0.0575
   0.750   0.5265   0.01882   0.00822  -0.0608   0.5933   0.0587
   1.000   0.5486   0.01870   0.00799  -0.0594   0.5766   0.0604
   1.250   0.5724   0.01866   0.00783  -0.0584   0.5608   0.0630
   1.500   0.5966   0.01868   0.00775  -0.0575   0.5454   0.0673
   1.750   0.6219   0.01869   0.00768  -0.0569   0.5296   0.0740
   2.000   0.6451   0.01873   0.00764  -0.0559   0.5120   0.0830
   2.500   0.8559   0.01817   0.00870  -0.0903   0.4451   1.0000
   2.750   0.8718   0.01844   0.00884  -0.0879   0.4281   1.0000
   3.000   0.8868   0.01874   0.00901  -0.0853   0.4091   1.0000
   3.250   0.8995   0.01907   0.00918  -0.0823   0.3865   1.0000
   3.500   0.9104   0.01945   0.00936  -0.0790   0.3639   1.0000
   3.750   0.9232   0.01983   0.00959  -0.0761   0.3464   1.0000
   4.000   0.9363   0.02023   0.00987  -0.0733   0.3299   1.0000
   4.250   0.9503   0.02062   0.01016  -0.0708   0.3163   1.0000
   4.500   0.9639   0.02105   0.01049  -0.0682   0.3033   1.0000
   4.750   0.9781   0.02147   0.01084  -0.0658   0.2902   1.0000
   5.000   0.9932   0.02189   0.01122  -0.0635   0.2793   1.0000
   5.250   1.0069   0.02236   0.01162  -0.0611   0.2676   1.0000
   5.500   1.0206   0.02284   0.01204  -0.0587   0.2545   1.0000
   5.750   1.0340   0.02336   0.01250  -0.0564   0.2406   1.0000
   6.000   1.0473   0.02389   0.01299  -0.0540   0.2284   1.0000
   6.250   1.0600   0.02446   0.01351  -0.0516   0.2166   1.0000
   6.500   1.0726   0.02506   0.01406  -0.0493   0.2035   1.0000
   6.750   1.0848   0.02570   0.01466  -0.0470   0.1900   1.0000
   7.000   1.0964   0.02639   0.01531  -0.0447   0.1766   1.0000
   7.250   1.1041   0.02731   0.01610  -0.0419   0.1548   1.0000
   7.500   1.1123   0.02824   0.01694  -0.0393   0.1358   1.0000
   7.750   1.1191   0.02929   0.01789  -0.0367   0.1172   1.0000
   8.000   1.1161   0.03105   0.01935  -0.0331   0.0836   1.0000
   8.250   1.1216   0.03230   0.02056  -0.0307   0.0787   1.0000
   8.500   1.1291   0.03345   0.02173  -0.0285   0.0764   1.0000
   8.750   1.1361   0.03467   0.02298  -0.0265   0.0751   1.0000
   9.000   1.1429   0.03593   0.02429  -0.0245   0.0740   1.0000
   9.250   1.1492   0.03727   0.02570  -0.0227   0.0733   1.0000
   9.500   1.1549   0.03870   0.02720  -0.0209   0.0726   1.0000
   9.750   1.1596   0.04025   0.02886  -0.0193   0.0721   1.0000
  10.000   1.1639   0.04191   0.03060  -0.0177   0.0718   1.0000
  10.250   1.1659   0.04383   0.03262  -0.0163   0.0712   1.0000
  10.500   1.1687   0.04576   0.03466  -0.0151   0.0711   1.0000
  10.750   1.1687   0.04805   0.03705  -0.0139   0.0707   1.0000
  11.000   1.1694   0.05038   0.03950  -0.0131   0.0705   1.0000
  11.250   1.1690   0.05290   0.04214  -0.0124   0.0704   1.0000
  11.500   1.1649   0.05594   0.04529  -0.0119   0.0700   1.0000
  11.750   1.1651   0.05861   0.04809  -0.0115   0.0701   1.0000
  12.000   1.1618   0.06177   0.05135  -0.0114   0.0698   1.0000
  12.250   1.1577   0.06511   0.05481  -0.0114   0.0697   1.0000
  12.500   1.1554   0.06832   0.05813  -0.0115   0.0697   1.0000
  12.750   1.1532   0.07157   0.06150  -0.0117   0.0697   1.0000
  13.000   1.1512   0.07483   0.06488  -0.0119   0.0696   1.0000
  13.250   1.1493   0.07810   0.06825  -0.0122   0.0695   1.0000
  13.500   1.1484   0.08127   0.07150  -0.0125   0.0694   1.0000
  13.750   1.1494   0.08416   0.07448  -0.0127   0.0694   1.0000
  14.000   1.1512   0.08693   0.07734  -0.0130   0.0694   1.0000
  14.250   1.1545   0.08948   0.07996  -0.0131   0.0693   1.0000
  14.500   1.1594   0.09175   0.08231  -0.0132   0.0693   1.0000
  14.750   1.1651   0.09393   0.08455  -0.0132   0.0692   1.0000
  15.000   1.1718   0.09595   0.08663  -0.0132   0.0692   1.0000
  15.250   1.1782   0.09800   0.08875  -0.0133   0.0689   1.0000
  15.500   1.1827   0.10045   0.09130  -0.0136   0.0686   1.0000
  15.750   1.1877   0.10280   0.09376  -0.0139   0.0682   1.0000
  16.000   1.1900   0.10565   0.09672  -0.0145   0.0676   1.0000
  16.250   1.1924   0.10847   0.09964  -0.0151   0.0668   1.0000
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