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Fage & Collins 3 (fg3-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 3 (fg3-il)
Reynolds number: 50,000
Max Cl/Cd: 35.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg3-il-50000-n5.txt
Download as CSV file: xf-fg3-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 3                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3590   0.10382   0.09777  -0.0290   1.0000   0.0999
  -7.750  -0.3815   0.10319   0.09729  -0.0277   1.0000   0.1007
  -7.500  -0.3995   0.10206   0.09625  -0.0280   1.0000   0.1012
  -7.250  -0.3855   0.09685   0.09110  -0.0237   1.0000   0.1047
  -7.000  -0.3877   0.09442   0.08873  -0.0215   1.0000   0.1095
  -6.750  -0.4002   0.09256   0.08691  -0.0213   1.0000   0.1140
  -6.500  -0.4180   0.09162   0.08598  -0.0239   1.0000   0.1165
  -6.250  -0.4090   0.08710   0.08157  -0.0188   1.0000   0.1219
  -6.000  -0.4123   0.08477   0.07926  -0.0181   1.0000   0.1281
  -5.750  -0.4191   0.08228   0.07675  -0.0195   1.0000   0.1335
  -5.500  -0.4151   0.07923   0.07377  -0.0161   1.0000   0.1412
  -5.250  -0.4167   0.07643   0.07094  -0.0164   1.0000   0.1504
  -4.750  -0.4104   0.07088   0.06538  -0.0139   1.0000   0.1685
  -4.500  -0.3885   0.06739   0.06180  -0.0167   0.9937   0.1887
  -4.250  -0.3678   0.06404   0.05841  -0.0183   0.9869   0.2179
  -3.750  -0.2721   0.05214   0.04483  -0.0320   0.9696   0.0882
  -3.500  -0.2359   0.04845   0.04038  -0.0334   0.9601   0.0723
  -3.250  -0.2032   0.04563   0.03705  -0.0347   0.9500   0.0713
  -3.000  -0.1690   0.04294   0.03383  -0.0360   0.9400   0.0715
  -2.750  -0.1344   0.04002   0.03059  -0.0376   0.9306   0.0703
  -2.500  -0.1027   0.03780   0.02796  -0.0381   0.9197   0.0695
  -2.250  -0.0677   0.03635   0.02586  -0.0387   0.9094   0.0717
  -2.000  -0.0269   0.03427   0.02343  -0.0407   0.9012   0.0725
  -1.750   0.0062   0.03283   0.02164  -0.0411   0.8898   0.0723
  -1.500   0.0431   0.03145   0.01998  -0.0423   0.8788   0.0726
  -1.250   0.0867   0.02998   0.01833  -0.0448   0.8697   0.0747
  -1.000   0.1327   0.02884   0.01703  -0.0478   0.8592   0.0794
  -0.500   0.2127   0.02707   0.01487  -0.0511   0.8338   0.0829
  -0.250   0.2480   0.02634   0.01397  -0.0518   0.8195   0.0852
   0.000   0.2824   0.02562   0.01313  -0.0525   0.8039   0.0880
   0.250   0.3169   0.02493   0.01237  -0.0532   0.7875   0.0931
   0.500   0.3527   0.02425   0.01166  -0.0540   0.7702   0.1055
   1.000   0.5085   0.02103   0.01039  -0.0734   0.7235   1.0000
   1.250   0.5419   0.02080   0.00985  -0.0736   0.6948   1.0000
   1.500   0.5742   0.02068   0.00943  -0.0738   0.6635   1.0000
   1.750   0.6055   0.02067   0.00910  -0.0739   0.6309   1.0000
   2.000   0.6350   0.02081   0.00890  -0.0738   0.6001   1.0000
   2.250   0.6625   0.02107   0.00884  -0.0734   0.5730   1.0000
   2.500   0.6881   0.02143   0.00893  -0.0729   0.5501   1.0000
   2.750   0.7132   0.02185   0.00909  -0.0723   0.5307   1.0000
   3.000   0.7373   0.02231   0.00936  -0.0716   0.5132   1.0000
   3.250   0.7621   0.02278   0.00970  -0.0712   0.4986   1.0000
   3.500   0.7873   0.02328   0.01004  -0.0708   0.4853   1.0000
   3.750   0.8123   0.02379   0.01047  -0.0704   0.4732   1.0000
   4.000   0.8370   0.02431   0.01098  -0.0700   0.4621   1.0000
   4.250   0.8630   0.02484   0.01146  -0.0699   0.4525   1.0000
   4.500   0.8889   0.02539   0.01199  -0.0698   0.4435   1.0000
   4.750   0.9133   0.02597   0.01263  -0.0694   0.4349   1.0000
   5.000   0.9398   0.02654   0.01318  -0.0694   0.4272   1.0000
   5.250   0.9629   0.02719   0.01394  -0.0688   0.4196   1.0000
   5.500   0.9886   0.02782   0.01461  -0.0687   0.4132   1.0000
   5.750   1.0120   0.02853   0.01546  -0.0682   0.4068   1.0000
   6.000   1.0348   0.02924   0.01629  -0.0676   0.4004   1.0000
   6.250   1.0606   0.02993   0.01704  -0.0675   0.3950   1.0000
   6.500   1.0792   0.03079   0.01814  -0.0663   0.3888   1.0000
   6.750   1.1025   0.03159   0.01911  -0.0658   0.3839   1.0000
   7.000   1.1260   0.03243   0.02010  -0.0654   0.3793   1.0000
   7.250   1.1419   0.03345   0.02141  -0.0638   0.3738   1.0000
   7.500   1.1633   0.03435   0.02249  -0.0631   0.3690   1.0000
   7.750   1.1865   0.03527   0.02362  -0.0626   0.3648   1.0000
   8.000   1.1980   0.03656   0.02527  -0.0605   0.3601   1.0000
   8.250   1.2148   0.03769   0.02668  -0.0591   0.3556   1.0000
   8.500   1.2379   0.03840   0.02755  -0.0585   0.3498   1.0000
   8.750   1.2469   0.03875   0.02808  -0.0554   0.3375   1.0000
   9.000   1.2532   0.03894   0.02847  -0.0518   0.3238   1.0000
   9.250   1.2576   0.03925   0.02896  -0.0480   0.3111   1.0000
   9.500   1.2593   0.03936   0.02922  -0.0438   0.2970   1.0000
   9.750   1.2539   0.03946   0.02941  -0.0385   0.2807   1.0000
  10.000   1.2441   0.03995   0.03003  -0.0329   0.2663   1.0000
  10.250   1.2319   0.04065   0.03083  -0.0275   0.2486   1.0000
  10.500   1.2245   0.04185   0.03220  -0.0235   0.2321   1.0000
  10.750   1.2154   0.04368   0.03430  -0.0202   0.2098   1.0000
  11.000   1.2063   0.04593   0.03669  -0.0177   0.1727   1.0000
  11.500   1.1605   0.05394   0.04376  -0.0138   0.0768   1.0000
  11.750   1.1374   0.05931   0.04908  -0.0137   0.0680   1.0000
  12.000   1.1184   0.06477   0.05464  -0.0144   0.0643   1.0000
  12.250   1.0983   0.07085   0.06082  -0.0158   0.0614   1.0000
  12.500   1.0818   0.07671   0.06684  -0.0173   0.0598   1.0000
  12.750   1.0656   0.08270   0.07295  -0.0190   0.0582   1.0000
  13.000   1.0495   0.08873   0.07907  -0.0207   0.0562   1.0000
  13.250   1.0357   0.09440   0.08480  -0.0223   0.0544   1.0000
  13.500   1.0222   0.10001   0.09045  -0.0239   0.0523   1.0000
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