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Fage & Collins 1 (fg1-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Fage & Collins 1 (fg1-il)
Reynolds number: 50,000
Max Cl/Cd: 37.88 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fg1-il-50000.txt
Download as CSV file: xf-fg1-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 1                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4332   0.11211   0.10496  -0.0226   1.0000   0.1864
  -9.000  -0.4090   0.10638   0.09920  -0.0202   1.0000   0.1994
  -8.750  -0.4345   0.10648   0.09949  -0.0210   1.0000   0.2022
  -8.500  -0.4130   0.10140   0.09439  -0.0188   1.0000   0.2159
  -8.250  -0.4116   0.09824   0.09132  -0.0177   1.0000   0.2231
  -8.000  -0.4233   0.09682   0.09003  -0.0164   1.0000   0.2323
  -7.750  -0.4157   0.09328   0.08654  -0.0146   1.0000   0.2423
  -7.500  -0.4434   0.09288   0.08632  -0.0140   1.0000   0.2495
  -7.250  -0.4325   0.08924   0.08272  -0.0112   1.0000   0.2631
  -7.000  -0.4311   0.08636   0.07991  -0.0090   1.0000   0.2763
  -6.750  -0.4338   0.08386   0.07749  -0.0068   1.0000   0.2903
  -6.500  -0.4368   0.08148   0.07519  -0.0044   1.0000   0.3063
  -6.250  -0.4414   0.07931   0.07310  -0.0018   1.0000   0.3255
  -6.000  -0.4577   0.07805   0.07193  -0.0004   1.0000   0.3456
  -5.750  -0.4457   0.07477   0.06873   0.0051   1.0000   0.3744
  -5.500  -0.4525   0.07299   0.06703   0.0094   1.0000   0.4086
  -5.250   0.0026   0.04855   0.04124  -0.0278   1.0000   1.0000
  -5.000   0.0107   0.04672   0.03949  -0.0279   1.0000   1.0000
  -4.750   0.0186   0.04498   0.03782  -0.0278   1.0000   1.0000
  -4.500   0.0136   0.04405   0.03702  -0.0245   1.0000   0.9949
  -4.250  -0.0482   0.04602   0.03929  -0.0081   1.0000   0.9571
  -4.000  -0.1057   0.04717   0.04070   0.0054   1.0000   0.9175
  -3.750  -0.1613   0.04763   0.04142   0.0169   1.0000   0.8742
  -3.500  -0.2157   0.04781   0.04183   0.0274   1.0000   0.8415
  -3.250  -0.2702   0.04748   0.04174   0.0371   1.0000   0.8106
  -3.000  -0.3250   0.04690   0.04138   0.0473   1.0000   0.7933
  -2.750  -0.3780   0.04580   0.04048   0.0566   1.0000   0.7775
  -2.500  -0.3963   0.04190   0.03636   0.0354   1.0000   0.6190
  -2.250  -0.2199   0.03560   0.02654  -0.0140   1.0000   0.2139
  -2.000  -0.1937   0.03393   0.02438  -0.0134   1.0000   0.1925
  -1.750  -0.1687   0.03261   0.02261  -0.0124   1.0000   0.1767
  -1.500  -0.1449   0.03158   0.02117  -0.0113   1.0000   0.1661
  -1.250  -0.1213   0.03061   0.01982  -0.0101   1.0000   0.1572
  -1.000  -0.0984   0.02989   0.01883  -0.0090   1.0000   0.1524
  -0.750  -0.0753   0.02905   0.01786  -0.0083   1.0000   0.1491
  -0.500  -0.0523   0.02843   0.01707  -0.0075   1.0000   0.1463
  -0.250  -0.0299   0.02800   0.01651  -0.0067   1.0000   0.1468
   0.000  -0.0028   0.02775   0.01612  -0.0069   1.0000   0.1486
   0.250   0.0227   0.02761   0.01589  -0.0069   1.0000   0.1511
   0.500   0.0460   0.02759   0.01580  -0.0067   1.0000   0.1526
   0.750   0.0666   0.02776   0.01590  -0.0063   1.0000   0.1544
   1.000   0.0869   0.02793   0.01613  -0.0062   1.0000   0.1586
   1.250   0.1057   0.02834   0.01656  -0.0060   1.0000   0.1648
   1.500   0.1638   0.02919   0.01763  -0.0132   0.9855   0.1957
   1.750   0.2618   0.02840   0.01865  -0.0276   0.9666   1.0000
   2.000   0.3209   0.02943   0.01937  -0.0343   0.9417   1.0000
   2.250   0.3784   0.03023   0.02001  -0.0405   0.9167   1.0000
   2.500   0.4416   0.03072   0.02045  -0.0471   0.8923   1.0000
   2.750   0.4997   0.03063   0.02036  -0.0519   0.8629   1.0000
   3.000   0.5626   0.02980   0.01962  -0.0564   0.8323   1.0000
   3.500   0.6757   0.02757   0.01765  -0.0622   0.7752   1.0000
   3.750   0.7309   0.02619   0.01642  -0.0645   0.7455   1.0000
   4.000   0.7885   0.02464   0.01500  -0.0667   0.7113   1.0000
   4.250   0.8316   0.02384   0.01419  -0.0669   0.6688   1.0000
   4.500   0.8718   0.02353   0.01372  -0.0669   0.6201   1.0000
   4.750   0.9053   0.02390   0.01384  -0.0663   0.5708   1.0000
   5.000   0.9307   0.02483   0.01455  -0.0649   0.5262   1.0000
   5.250   0.9536   0.02596   0.01553  -0.0634   0.4886   1.0000
   5.500   0.9758   0.02710   0.01657  -0.0620   0.4573   1.0000
   5.750   0.9995   0.02817   0.01753  -0.0608   0.4304   1.0000
   6.000   1.0161   0.02929   0.01874  -0.0586   0.4059   1.0000
   6.250   1.0390   0.03032   0.01965  -0.0573   0.3835   1.0000
   6.500   1.0547   0.03149   0.02097  -0.0550   0.3623   1.0000
   6.750   1.0741   0.03265   0.02217  -0.0533   0.3416   1.0000
   7.000   1.0938   0.03388   0.02337  -0.0516   0.3210   1.0000
   7.250   1.1077   0.03531   0.02497  -0.0491   0.3006   1.0000
   7.500   1.1252   0.03671   0.02640  -0.0472   0.2801   1.0000
   7.750   1.1417   0.03827   0.02795  -0.0451   0.2599   1.0000
   8.000   1.1526   0.04013   0.03006  -0.0423   0.2415   1.0000
   8.250   1.1652   0.04185   0.03186  -0.0397   0.2225   1.0000
   8.500   1.1827   0.04349   0.03337  -0.0380   0.2031   1.0000
   8.750   1.1920   0.04558   0.03556  -0.0352   0.1863   1.0000
   9.000   1.1989   0.04779   0.03791  -0.0322   0.1710   1.0000
   9.250   1.2074   0.05013   0.04035  -0.0296   0.1569   1.0000
   9.500   1.1959   0.05341   0.04425  -0.0246   0.1504   1.0000
   9.750   1.2021   0.05609   0.04699  -0.0221   0.1404   1.0000
  10.000   1.1862   0.05980   0.05116  -0.0175   0.1369   1.0000
  10.250   1.2017   0.06244   0.05369  -0.0162   0.1280   1.0000
  10.500   1.1790   0.06642   0.05807  -0.0117   0.1271   1.0000
  10.750   1.1534   0.07039   0.06231  -0.0074   0.1268   1.0000
  11.000   1.1260   0.07453   0.06664  -0.0038   0.1270   1.0000
  11.250   1.0998   0.07935   0.07161  -0.0019   0.1276   1.0000
  11.500   1.0725   0.08486   0.07724  -0.0014   0.1282   1.0000
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