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Fage & Collins 2 (fg2-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 2 (fg2-il)
Reynolds number: 50,000
Max Cl/Cd: 37.75 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg2-il-50000-n5.txt
Download as CSV file: xf-fg2-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Fage & Collins 2                                
  
 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  -0.4042   0.09804   0.09146  -0.0212   1.0000   0.1045
  -7.750  -0.4168   0.09635   0.08990  -0.0233   1.0000   0.1072
  -7.500  -0.4272   0.09469   0.08831  -0.0277   1.0000   0.1083
  -7.250  -0.4091   0.08927   0.08295  -0.0214   1.0000   0.1177
  -7.000  -0.4196   0.08765   0.08138  -0.0263   1.0000   0.1228
  -6.750  -0.4098   0.08309   0.07691  -0.0226   1.0000   0.1277
  -6.500  -0.4118   0.08077   0.07460  -0.0249   1.0000   0.1371
  -6.250  -0.4066   0.07692   0.07082  -0.0235   1.0000   0.1413
  -6.000  -0.4069   0.07488   0.06870  -0.0261   1.0000   0.1534
  -5.750  -0.3974   0.07072   0.06467  -0.0222   1.0000   0.1591
  -5.500  -0.3934   0.06777   0.06172  -0.0218   1.0000   0.1726
  -5.250  -0.3884   0.06503   0.05902  -0.0202   1.0000   0.1909
  -4.750  -0.3820   0.05990   0.05396  -0.0157   1.0000   0.2468
  -4.250  -0.3114   0.04813   0.04061  -0.0255   1.0000   0.0769
  -4.000  -0.2975   0.04506   0.03738  -0.0242   1.0000   0.0731
  -3.750  -0.2819   0.04247   0.03446  -0.0229   1.0000   0.0730
  -3.500  -0.2655   0.04009   0.03174  -0.0214   1.0000   0.0733
  -3.250  -0.2482   0.03778   0.02909  -0.0199   1.0000   0.0714
  -3.000  -0.2296   0.03562   0.02648  -0.0183   1.0000   0.0692
  -2.750  -0.2108   0.03382   0.02428  -0.0167   1.0000   0.0683
  -2.500  -0.1879   0.03235   0.02252  -0.0162   0.9979   0.0714
  -2.250  -0.1462   0.03061   0.02027  -0.0189   0.9881   0.0728
  -2.000  -0.1042   0.02900   0.01823  -0.0214   0.9778   0.0723
  -1.750  -0.0624   0.02760   0.01645  -0.0239   0.9659   0.0724
  -1.500  -0.0199   0.02638   0.01493  -0.0264   0.9521   0.0737
  -1.250   0.0250   0.02546   0.01368  -0.0293   0.9362   0.0786
  -1.000   0.0748   0.02426   0.01232  -0.0331   0.9208   0.0808
  -0.750   0.1207   0.02331   0.01121  -0.0361   0.9046   0.0827
  -0.500   0.1645   0.02251   0.01028  -0.0388   0.8881   0.0855
  -0.250   0.2073   0.02185   0.00947  -0.0412   0.8716   0.0894
   0.000   0.2471   0.02132   0.00883  -0.0432   0.8523   0.0955
   0.250   0.2870   0.02081   0.00834  -0.0452   0.8319   0.1095
   0.750   0.4250   0.01805   0.00755  -0.0615   0.7902   1.0000
   1.000   0.4628   0.01805   0.00727  -0.0630   0.7643   1.0000
   1.250   0.4991   0.01810   0.00706  -0.0642   0.7391   1.0000
   1.500   0.5308   0.01825   0.00701  -0.0645   0.7137   1.0000
   1.750   0.5606   0.01847   0.00702  -0.0646   0.6900   1.0000
   2.000   0.5891   0.01874   0.00710  -0.0644   0.6681   1.0000
   2.250   0.6159   0.01907   0.00728  -0.0640   0.6472   1.0000
   2.500   0.6424   0.01943   0.00754  -0.0636   0.6275   1.0000
   2.750   0.6690   0.01982   0.00783  -0.0633   0.6093   1.0000
   3.000   0.6954   0.02023   0.00816  -0.0629   0.5925   1.0000
   3.250   0.7212   0.02066   0.00857  -0.0625   0.5765   1.0000
   3.500   0.7465   0.02111   0.00901  -0.0620   0.5612   1.0000
   3.750   0.7721   0.02157   0.00948  -0.0616   0.5470   1.0000
   4.000   0.7969   0.02206   0.01004  -0.0610   0.5335   1.0000
   4.250   0.8208   0.02256   0.01061  -0.0603   0.5201   1.0000
   4.500   0.8437   0.02302   0.01112  -0.0594   0.5053   1.0000
   4.750   0.8654   0.02343   0.01154  -0.0581   0.4888   1.0000
   5.000   0.8849   0.02382   0.01203  -0.0564   0.4706   1.0000
   5.250   0.9045   0.02422   0.01251  -0.0548   0.4533   1.0000
   5.500   0.9253   0.02467   0.01306  -0.0534   0.4386   1.0000
   5.750   0.9464   0.02515   0.01366  -0.0522   0.4248   1.0000
   6.000   0.9672   0.02565   0.01433  -0.0509   0.4112   1.0000
   6.250   0.9876   0.02616   0.01498  -0.0495   0.3973   1.0000
   6.500   1.0077   0.02670   0.01567  -0.0481   0.3832   1.0000
   6.750   1.0277   0.02728   0.01641  -0.0466   0.3693   1.0000
   7.000   1.0476   0.02792   0.01727  -0.0452   0.3555   1.0000
   7.250   1.0668   0.02862   0.01816  -0.0437   0.3410   1.0000
   7.500   1.0836   0.02933   0.01909  -0.0418   0.3243   1.0000
   7.750   1.0930   0.02969   0.01951  -0.0386   0.2989   1.0000
   8.000   1.1002   0.03017   0.02012  -0.0353   0.2710   1.0000
   8.250   1.1125   0.03088   0.02104  -0.0329   0.2509   1.0000
   8.500   1.1240   0.03162   0.02210  -0.0304   0.2300   1.0000
   8.750   1.1264   0.03245   0.02282  -0.0268   0.1925   1.0000
   9.000   1.1225   0.03404   0.02402  -0.0230   0.1506   1.0000
   9.250   1.1202   0.03593   0.02581  -0.0195   0.1169   1.0000
   9.500   1.1162   0.03801   0.02785  -0.0159   0.0778   1.0000
   9.750   1.1060   0.04062   0.03020  -0.0125   0.0614   1.0000
  10.000   1.0967   0.04338   0.03291  -0.0097   0.0537   1.0000
  10.250   1.0866   0.04644   0.03597  -0.0076   0.0493   1.0000
  10.500   1.0801   0.04947   0.03917  -0.0064   0.0461   1.0000
  10.750   1.0713   0.05302   0.04287  -0.0057   0.0433   1.0000
  11.000   1.0625   0.05687   0.04685  -0.0057   0.0416   1.0000
  11.250   1.0551   0.06080   0.05091  -0.0061   0.0406   1.0000
  11.500   1.0480   0.06487   0.05507  -0.0066   0.0395   1.0000
  11.750   1.0441   0.06860   0.05901  -0.0070   0.0383   1.0000
  12.000   1.0409   0.07231   0.06289  -0.0073   0.0374   1.0000
  12.250   1.0373   0.07616   0.06692  -0.0077   0.0360   1.0000
  12.500   1.0336   0.08009   0.07100  -0.0083   0.0348   1.0000
  12.750   1.0308   0.08393   0.07498  -0.0089   0.0339   1.0000
  13.000   1.0259   0.08809   0.07925  -0.0099   0.0326   1.0000
  13.250   1.0230   0.09195   0.08315  -0.0104   0.0318   1.0000
  13.500   1.0186   0.09658   0.08805  -0.0116   0.0309   1.0000
  13.750   1.0138   0.10134   0.09304  -0.0130   0.0305   1.0000
  14.000   1.0068   0.10674   0.09867  -0.0149   0.0301   1.0000
  14.250   0.9995   0.11235   0.10448  -0.0171   0.0301   1.0000
  14.500   0.9894   0.11878   0.11112  -0.0199   0.0301   1.0000
  14.750   0.9779   0.12588   0.11839  -0.0233   0.0302   1.0000
  15.000   0.9653   0.13359   0.12625  -0.0272   0.0304   1.0000
  15.250   0.9525   0.14182   0.13459  -0.0313   0.0307   1.0000
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