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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 500,000
Max Cl/Cd: 62.16 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg4-il-500000.txt
Download as CSV file: xf-fg4-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1226   0.08927   0.08702  -0.0606   0.9777   0.0271
  -9.750  -0.1112   0.08565   0.08340  -0.0628   0.9764   0.0272
  -9.500  -0.0994   0.08197   0.07973  -0.0652   0.9753   0.0275
  -9.250  -0.0958   0.07883   0.07660  -0.0658   0.9694   0.0279
  -9.000  -0.0870   0.07499   0.07277  -0.0683   0.9669   0.0282
  -8.750  -0.0774   0.07091   0.06869  -0.0713   0.9651   0.0287
  -8.500  -0.0774   0.06767   0.06546  -0.0719   0.9577   0.0290
  -8.250  -0.0704   0.06334   0.06114  -0.0754   0.9547   0.0296
  -8.000  -0.0752   0.05906   0.05687  -0.0783   0.9467   0.0302
  -7.750  -0.0897   0.05325   0.05101  -0.0852   0.9395   0.0306
  -7.500  -0.0937   0.04604   0.04359  -0.0919   0.9326   0.0308
  -7.250  -0.0830   0.04077   0.03825  -0.0941   0.9301   0.0310
  -7.000  -0.0691   0.03791   0.03539  -0.0944   0.9245   0.0312
  -6.750  -0.0487   0.03475   0.03218  -0.0962   0.9204   0.0314
  -6.500  -0.0220   0.03129   0.02864  -0.0996   0.9176   0.0317
  -6.250   0.0045   0.02802   0.02527  -0.1027   0.9129   0.0323
  -6.000   0.0310   0.02480   0.02191  -0.1055   0.9067   0.0331
  -5.750   0.0020   0.03781   0.03465  -0.1007   0.9101   0.0330
  -5.500   0.0337   0.03390   0.02993  -0.1018   0.9038   0.0356
  -5.250   0.0710   0.02998   0.02606  -0.1064   0.8994   0.0361
  -5.000   0.0941   0.02851   0.02455  -0.1064   0.8899   0.0365
  -4.750   0.1293   0.02688   0.02279  -0.1090   0.8809   0.0372
  -4.500   0.1599   0.02535   0.02109  -0.1101   0.8690   0.0384
  -4.250   0.1658   0.02553   0.02066  -0.1034   0.8527   0.0411
  -4.000   0.1684   0.02276   0.01791  -0.0990   0.8362   0.0417
  -3.750   0.1764   0.02177   0.01688  -0.0949   0.8152   0.0422
  -3.500   0.1871   0.02090   0.01589  -0.0913   0.7862   0.0428
  -3.250   0.2038   0.02013   0.01490  -0.0888   0.7543   0.0438
  -3.000   0.2213   0.02106   0.01524  -0.0851   0.7251   0.0474
  -2.750   0.2325   0.01866   0.01270  -0.0822   0.7002   0.0485
  -2.500   0.2486   0.01797   0.01190  -0.0798   0.6791   0.0495
  -2.250   0.2646   0.01744   0.01124  -0.0771   0.6610   0.0507
  -2.000   0.2778   0.01725   0.01068  -0.0733   0.6441   0.0558
  -1.750   0.2948   0.01634   0.00977  -0.0712   0.6280   0.0574
  -1.500   0.3112   0.01596   0.00929  -0.0686   0.6116   0.0599
  -1.250   0.3272   0.01555   0.00869  -0.0658   0.5988   0.0657
  -1.000   0.3445   0.01508   0.00818  -0.0635   0.5840   0.0684
  -0.250   0.4105   0.01350   0.00588  -0.0572   0.5471   0.0477
   0.000   0.4360   0.01258   0.00495  -0.0564   0.5353   0.0434
   0.250   0.4577   0.01229   0.00455  -0.0547   0.5234   0.0419
   0.500   0.4768   0.01212   0.00433  -0.0527   0.5098   0.0419
   0.750   0.4955   0.01202   0.00417  -0.0505   0.4973   0.0418
   1.000   0.5129   0.01190   0.00399  -0.0482   0.4804   0.0420
   1.250   0.5301   0.01182   0.00387  -0.0458   0.4628   0.0425
   1.500   0.5472   0.01181   0.00379  -0.0434   0.4447   0.0432
   1.750   0.5623   0.01188   0.00376  -0.0407   0.4159   0.0437
   2.000   0.5756   0.01211   0.00382  -0.0377   0.3801   0.0458
   2.250   0.5896   0.01237   0.00388  -0.0348   0.3450   0.0470
   2.500   0.6050   0.01264   0.00398  -0.0323   0.3138   0.0470
   2.750   0.6227   0.01280   0.00402  -0.0303   0.2910   0.0506
   3.000   0.6388   0.01313   0.00417  -0.0281   0.2592   0.0522
   3.250   0.6558   0.01342   0.00432  -0.0260   0.2331   0.0569
   3.500   0.9240   0.01489   0.00683  -0.0828   0.0625   1.0000
   3.750   0.9413   0.01515   0.00707  -0.0807   0.0616   1.0000
   4.000   0.9585   0.01542   0.00734  -0.0787   0.0608   1.0000
   4.250   0.9753   0.01573   0.00766  -0.0765   0.0599   1.0000
   4.500   0.9924   0.01604   0.00796  -0.0745   0.0594   1.0000
   4.750   1.0082   0.01640   0.00833  -0.0723   0.0585   1.0000
   5.000   1.0246   0.01673   0.00867  -0.0702   0.0583   1.0000
   5.250   1.0401   0.01712   0.00907  -0.0679   0.0577   1.0000
   5.500   1.0543   0.01758   0.00955  -0.0655   0.0571   1.0000
   5.750   1.0683   0.01805   0.01003  -0.0631   0.0567   1.0000
   6.000   1.0833   0.01846   0.01047  -0.0609   0.0564   1.0000
   6.250   1.0980   0.01890   0.01092  -0.0587   0.0563   1.0000
   6.500   1.1115   0.01941   0.01145  -0.0564   0.0560   1.0000
   6.750   1.1248   0.01992   0.01199  -0.0540   0.0560   1.0000
   7.000   1.1377   0.02047   0.01257  -0.0517   0.0560   1.0000
   7.250   1.1504   0.02104   0.01318  -0.0494   0.0558   1.0000
   7.500   1.1617   0.02170   0.01387  -0.0470   0.0556   1.0000
   7.750   1.1727   0.02239   0.01459  -0.0446   0.0556   1.0000
   8.000   1.1828   0.02315   0.01539  -0.0422   0.0554   1.0000
   8.250   1.1929   0.02394   0.01623  -0.0399   0.0554   1.0000
   8.500   1.2025   0.02479   0.01712  -0.0377   0.0554   1.0000
   8.750   1.2114   0.02572   0.01809  -0.0354   0.0553   1.0000
   9.000   1.2209   0.02664   0.01905  -0.0334   0.0552   1.0000
   9.250   1.2290   0.02769   0.02015  -0.0313   0.0550   1.0000
   9.500   1.2372   0.02877   0.02127  -0.0293   0.0545   1.0000
   9.750   1.2454   0.02988   0.02243  -0.0275   0.0543   1.0000
  10.000   1.2515   0.03119   0.02379  -0.0256   0.0535   1.0000
  10.250   1.2589   0.03246   0.02510  -0.0239   0.0533   1.0000
  10.500   1.2653   0.03385   0.02653  -0.0223   0.0530   1.0000
  10.750   1.2713   0.03532   0.02806  -0.0208   0.0527   1.0000
  11.000   1.2775   0.03684   0.02962  -0.0195   0.0525   1.0000
  11.250   1.2825   0.03850   0.03133  -0.0182   0.0520   1.0000
  11.500   1.2876   0.04023   0.03310  -0.0170   0.0518   1.0000
  11.750   1.2904   0.04217   0.03505  -0.0158   0.0511   1.0000
  12.000   1.2984   0.04371   0.03665  -0.0149   0.0513   1.0000
  12.250   1.3034   0.04551   0.03847  -0.0139   0.0509   1.0000
  12.500   1.3102   0.04714   0.04011  -0.0128   0.0505   1.0000
  12.750   1.3204   0.04847   0.04143  -0.0116   0.0501   1.0000
  13.000   1.3273   0.05017   0.04320  -0.0110   0.0497   1.0000
  13.250   1.3295   0.05245   0.04561  -0.0109   0.0493   1.0000
  13.500   1.3346   0.05448   0.04773  -0.0107   0.0490   1.0000
  13.750   1.3404   0.05645   0.04977  -0.0104   0.0487   1.0000
  14.000   1.3454   0.05855   0.05194  -0.0103   0.0484   1.0000
  14.250   1.3490   0.06085   0.05433  -0.0103   0.0478   1.0000
  14.500   1.3525   0.06320   0.05675  -0.0103   0.0473   1.0000
  14.750   1.3569   0.06542   0.05904  -0.0103   0.0470   1.0000
  15.000   1.3585   0.06808   0.06177  -0.0106   0.0462   1.0000
  15.250   1.3612   0.07058   0.06433  -0.0108   0.0458   1.0000
  15.500   1.3609   0.07353   0.06731  -0.0113   0.0448   1.0000
  15.750   1.3652   0.07575   0.06956  -0.0113   0.0445   1.0000
  16.000   1.3729   0.07712   0.07091  -0.0104   0.0435   1.0000
  16.250   1.3710   0.08052   0.07443  -0.0114   0.0433   1.0000
  16.500   1.3667   0.08446   0.07852  -0.0128   0.0428   1.0000
  16.750   1.3660   0.08781   0.08197  -0.0138   0.0425   1.0000
  17.000   1.3597   0.09228   0.08659  -0.0156   0.0416   1.0000
  17.250   1.3586   0.09569   0.09009  -0.0167   0.0411   1.0000
  17.500   1.3552   0.09966   0.09417  -0.0181   0.0405   1.0000
  17.750   1.3512   0.10381   0.09841  -0.0198   0.0398   1.0000
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