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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 50,000
Max Cl/Cd: 30.49 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg4-il-50000.txt
Download as CSV file: xf-fg4-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.2593   0.15511   0.14819  -0.0324   1.0000   0.1337
 -12.750  -0.3199   0.15406   0.14640  -0.0297   1.0000   0.1327
 -12.500  -0.3359   0.15525   0.14771  -0.0314   1.0000   0.1336
 -12.250  -0.3062   0.14638   0.13883  -0.0292   1.0000   0.1370
 -12.000  -0.2960   0.14282   0.13530  -0.0284   1.0000   0.1414
 -11.750  -0.2939   0.14052   0.13306  -0.0283   1.0000   0.1458
 -11.500  -0.3008   0.13961   0.13223  -0.0289   1.0000   0.1497
 -11.250  -0.3191   0.14044   0.13319  -0.0301   1.0000   0.1514
  -5.500  -0.4654   0.09217   0.08698   0.0073   1.0000   0.2839
  -5.250  -0.4558   0.08883   0.08377   0.0119   1.0000   0.2932
  -5.000  -0.4723   0.08730   0.08230   0.0131   1.0000   0.3065
  -4.750  -0.4836   0.08602   0.08104   0.0147   1.0000   0.3239
  -4.500   0.0838   0.06412   0.05850  -0.0204   1.0000   1.0000
  -4.250   0.0790   0.06366   0.05817  -0.0185   1.0000   1.0000
  -4.000   0.0722   0.06342   0.05807  -0.0165   1.0000   1.0000
  -3.750   0.0643   0.06338   0.05815  -0.0146   1.0000   1.0000
  -3.500   0.0558   0.06340   0.05830  -0.0127   1.0000   1.0000
  -3.250   0.0479   0.06345   0.05846  -0.0110   1.0000   1.0000
  -3.000   0.0252   0.06312   0.05829  -0.0065   0.9885   0.9793
  -2.750  -0.0271   0.06296   0.05825   0.0030   0.9667   0.9234
  -2.500  -0.0831   0.06257   0.05797   0.0117   0.9495   0.8746
  -2.250  -0.1374   0.06150   0.05701   0.0187   0.9340   0.8279
  -2.000  -0.1956   0.06031   0.05593   0.0273   0.9207   0.8038
  -1.750  -0.2532   0.05884   0.05456   0.0367   0.9083   0.7877
  -1.500  -0.3081   0.05699   0.05277   0.0442   0.8974   0.7669
  -1.250  -0.1688   0.05414   0.04657  -0.0159   0.8767   0.2839
  -1.000  -0.1208   0.05241   0.04409  -0.0188   0.8654   0.2241
  -0.750  -0.0839   0.05101   0.04220  -0.0197   0.8532   0.1971
  -0.500  -0.0592   0.05040   0.04119  -0.0189   0.8406   0.1821
  -0.250  -0.0248   0.05017   0.04033  -0.0190   0.8285   0.1695
   0.000   0.0250   0.04887   0.03883  -0.0221   0.8171   0.1654
   0.250   0.0492   0.04843   0.03821  -0.0217   0.8033   0.1630
   0.500   0.0812   0.04806   0.03759  -0.0222   0.7899   0.1586
   0.750   0.1248   0.04775   0.03698  -0.0246   0.7769   0.1550
   1.000   0.2083   0.04698   0.03598  -0.0338   0.7630   0.1548
   1.250   0.2841   0.04599   0.03497  -0.0412   0.7499   0.1638
   1.500   0.3159   0.04615   0.03505  -0.0421   0.7347   0.1699
   1.750   0.5151   0.04186   0.03320  -0.0718   0.7193   1.0000
   2.000   0.5442   0.04220   0.03312  -0.0709   0.7047   1.0000
   2.250   0.6194   0.04020   0.03066  -0.0753   0.6967   1.0000
   2.500   0.6379   0.04084   0.03116  -0.0735   0.6805   1.0000
   2.750   0.6570   0.04152   0.03172  -0.0719   0.6650   1.0000
   3.000   0.6842   0.04185   0.03195  -0.0712   0.6507   1.0000
   3.250   0.7840   0.03863   0.02855  -0.0792   0.6390   1.0000
   3.500   0.8454   0.03686   0.02665  -0.0824   0.6206   1.0000
   3.750   0.8882   0.03589   0.02556  -0.0831   0.6012   1.0000
   4.000   0.9267   0.03524   0.02480  -0.0835   0.5824   1.0000
   4.250   0.9611   0.03487   0.02431  -0.0834   0.5645   1.0000
   4.500   0.9950   0.03467   0.02402  -0.0835   0.5481   1.0000
   4.750   1.0335   0.03443   0.02363  -0.0845   0.5329   1.0000
   5.000   1.0349   0.03552   0.02478  -0.0800   0.5186   1.0000
   5.250   1.0442   0.03651   0.02579  -0.0769   0.5059   1.0000
   5.500   1.0710   0.03663   0.02585  -0.0762   0.4922   1.0000
   5.750   1.1080   0.03634   0.02543  -0.0769   0.4785   1.0000
   6.000   1.1076   0.03738   0.02657  -0.0722   0.4655   1.0000
   6.250   1.1179   0.03811   0.02733  -0.0692   0.4534   1.0000
   6.500   1.1441   0.03798   0.02712  -0.0683   0.4402   1.0000
   6.750   1.1597   0.03856   0.02772  -0.0662   0.4294   1.0000
   7.000   1.1644   0.03969   0.02893  -0.0627   0.4198   1.0000
   7.250   1.2008   0.03952   0.02870  -0.0636   0.4098   1.0000
   7.500   1.1878   0.04137   0.03074  -0.0576   0.4010   1.0000
   7.750   1.2214   0.04111   0.03040  -0.0580   0.3904   1.0000
   8.000   1.2141   0.04256   0.03199  -0.0529   0.3810   1.0000
   8.250   1.2297   0.04286   0.03231  -0.0507   0.3702   1.0000
   8.500   1.2666   0.04228   0.03160  -0.0515   0.3578   1.0000
   8.750   1.2403   0.04426   0.03381  -0.0437   0.3496   1.0000
   9.000   1.2566   0.04417   0.03366  -0.0415   0.3367   1.0000
   9.250   1.2752   0.04397   0.03336  -0.0396   0.3225   1.0000
   9.500   1.2647   0.04531   0.03487  -0.0344   0.3113   1.0000
   9.750   1.2625   0.04649   0.03612  -0.0306   0.2994   1.0000
  10.000   1.2624   0.04725   0.03685  -0.0269   0.2838   1.0000
  10.250   1.2617   0.04833   0.03790  -0.0235   0.2683   1.0000
  10.500   1.2557   0.04983   0.03935  -0.0198   0.2518   1.0000
  10.750   1.2484   0.05170   0.04116  -0.0165   0.2352   1.0000
  11.000   1.2476   0.05355   0.04291  -0.0140   0.2208   1.0000
  11.250   1.2563   0.05498   0.04418  -0.0123   0.2080   1.0000
  11.500   1.2370   0.05880   0.04822  -0.0097   0.2001   1.0000
  11.750   1.2532   0.06005   0.04934  -0.0087   0.1918   1.0000
  12.000   1.2324   0.06456   0.05414  -0.0069   0.1877   1.0000
  12.250   1.2238   0.06830   0.05802  -0.0058   0.1838   1.0000
  12.500   1.2647   0.06783   0.05731  -0.0054   0.1784   1.0000
  12.750   1.2249   0.07449   0.06434  -0.0044   0.1772   1.0000
  13.000   1.1639   0.08472   0.07492  -0.0054   0.1769   1.0000
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