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Fage & Collins 4 (fg4-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Fage & Collins 4 (fg4-il)
Reynolds number: 50,000
Max Cl/Cd: 32.84 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fg4-il-50000-n5.txt
Download as CSV file: xf-fg4-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3528   0.10448   0.09829  -0.0182   1.0000   0.1366
  -7.500  -0.3838   0.10406   0.09800  -0.0164   1.0000   0.1386
  -7.250  -0.3971   0.10176   0.09571  -0.0227   0.9934   0.1410
  -7.000  -0.3652   0.09686   0.09089  -0.0197   0.9910   0.1449
  -6.500  -0.3391   0.08974   0.08372  -0.0297   0.9696   0.1615
  -6.250  -0.3140   0.08628   0.08030  -0.0296   0.9633   0.1690
  -6.000  -0.3069   0.08276   0.07673  -0.0341   0.9496   0.1815
  -5.750  -0.2828   0.07948   0.07347  -0.0352   0.9420   0.1910
  -5.500  -0.2695   0.07611   0.07007  -0.0372   0.9305   0.2040
  -5.000  -0.2430   0.07057   0.06447  -0.0393   0.9078   0.2408
  -4.750  -0.2193   0.06747   0.06140  -0.0400   0.9009   0.2624
  -4.500  -0.1775   0.06004   0.05269  -0.0510   0.8865   0.1205
  -4.250  -0.1593   0.05568   0.04777  -0.0505   0.8746   0.0914
  -4.000  -0.1293   0.05276   0.04477  -0.0517   0.8682   0.0864
  -3.750  -0.1156   0.05068   0.04249  -0.0500   0.8552   0.0846
  -3.500  -0.0959   0.04861   0.04016  -0.0490   0.8447   0.0834
  -3.250  -0.0721   0.04642   0.03761  -0.0484   0.8356   0.0811
  -3.000  -0.0549   0.04520   0.03568  -0.0457   0.8231   0.0774
  -2.750  -0.0239   0.04293   0.03329  -0.0463   0.8167   0.0762
  -2.500  -0.0090   0.04163   0.03182  -0.0440   0.8040   0.0753
  -2.250   0.0152   0.04015   0.03010  -0.0430   0.7947   0.0744
  -2.000   0.0420   0.03870   0.02837  -0.0423   0.7858   0.0735
  -1.750   0.0656   0.03757   0.02700  -0.0411   0.7755   0.0728
  -1.500   0.0995   0.03612   0.02527  -0.0413   0.7681   0.0722
  -1.250   0.1251   0.03519   0.02411  -0.0404   0.7575   0.0729
  -1.000   0.1645   0.03393   0.02260  -0.0415   0.7504   0.0746
  -0.750   0.1936   0.03321   0.02166  -0.0412   0.7397   0.0759
  -0.500   0.2406   0.03190   0.02016  -0.0437   0.7325   0.0767
  -0.250   0.2833   0.03111   0.01919  -0.0459   0.7218   0.0774
   0.000   0.3484   0.02969   0.01771  -0.0521   0.7142   0.0795
   0.250   0.3845   0.02915   0.01712  -0.0533   0.7026   0.0821
   0.500   0.4349   0.02829   0.01612  -0.0568   0.6940   0.0879
   0.750   0.4625   0.02808   0.01585  -0.0565   0.6811   0.0921
   1.000   0.5095   0.02743   0.01512  -0.0596   0.6711   0.0990
   1.250   0.5408   0.02724   0.01489  -0.0599   0.6581   0.1080
   1.500   0.5751   0.02693   0.01476  -0.0611   0.6452   0.1401
   1.750   0.7337   0.02505   0.01456  -0.0872   0.6257   1.0000
   2.000   0.7598   0.02521   0.01450  -0.0865   0.6108   1.0000
   2.250   0.7844   0.02536   0.01443  -0.0855   0.5945   1.0000
   2.500   0.8061   0.02553   0.01441  -0.0839   0.5772   1.0000
   2.750   0.8246   0.02574   0.01445  -0.0817   0.5590   1.0000
   3.000   0.8410   0.02606   0.01464  -0.0793   0.5423   1.0000
   3.250   0.8557   0.02640   0.01488  -0.0767   0.5255   1.0000
   3.500   0.8706   0.02676   0.01515  -0.0741   0.5091   1.0000
   3.750   0.8858   0.02714   0.01543  -0.0717   0.4936   1.0000
   4.000   0.9004   0.02750   0.01569  -0.0691   0.4777   1.0000
   4.250   0.9145   0.02787   0.01596  -0.0665   0.4624   1.0000
   4.500   0.9284   0.02827   0.01630  -0.0639   0.4485   1.0000
   4.750   0.9387   0.02875   0.01674  -0.0608   0.4338   1.0000
   5.000   0.9512   0.02923   0.01718  -0.0582   0.4205   1.0000
   5.250   0.9647   0.02968   0.01758  -0.0557   0.4078   1.0000
   5.500   0.9775   0.03018   0.01801  -0.0531   0.3950   1.0000
   5.750   0.9883   0.03077   0.01858  -0.0504   0.3818   1.0000
   6.000   1.0008   0.03135   0.01911  -0.0480   0.3701   1.0000
   6.250   1.0139   0.03193   0.01964  -0.0458   0.3594   1.0000
   6.500   1.0256   0.03265   0.02040  -0.0435   0.3488   1.0000
   6.750   1.0383   0.03330   0.02098  -0.0413   0.3391   1.0000
   7.000   1.0492   0.03411   0.02184  -0.0391   0.3293   1.0000
   7.250   1.0598   0.03488   0.02259  -0.0368   0.3195   1.0000
   7.500   1.0687   0.03578   0.02353  -0.0344   0.3091   1.0000
   7.750   1.0774   0.03672   0.02449  -0.0322   0.2994   1.0000
   8.000   1.0850   0.03772   0.02549  -0.0299   0.2893   1.0000
   8.250   1.0928   0.03884   0.02670  -0.0278   0.2805   1.0000
   8.500   1.1011   0.03995   0.02789  -0.0259   0.2727   1.0000
   8.750   1.1081   0.04120   0.02922  -0.0240   0.2645   1.0000
   9.000   1.1134   0.04257   0.03066  -0.0221   0.2556   1.0000
   9.250   1.1162   0.04414   0.03231  -0.0201   0.2451   1.0000
   9.500   1.1190   0.04576   0.03394  -0.0183   0.2354   1.0000
   9.750   1.1195   0.04773   0.03604  -0.0168   0.2240   1.0000
  10.000   1.1191   0.04983   0.03819  -0.0153   0.2123   1.0000
  10.250   1.1174   0.05213   0.04053  -0.0141   0.2003   1.0000
  10.500   1.1175   0.05454   0.04307  -0.0132   0.1903   1.0000
  10.750   1.1152   0.05722   0.04584  -0.0124   0.1788   1.0000
  11.000   1.1127   0.06003   0.04869  -0.0118   0.1686   1.0000
  11.250   1.1092   0.06308   0.05179  -0.0114   0.1582   1.0000
  11.500   1.1039   0.06645   0.05520  -0.0111   0.1471   1.0000
  11.750   1.0997   0.06975   0.05852  -0.0110   0.1401   1.0000
  12.000   1.0948   0.07327   0.06210  -0.0110   0.1327   1.0000
  12.250   1.0889   0.07695   0.06576  -0.0111   0.1265   1.0000
  12.500   1.0851   0.08050   0.06938  -0.0114   0.1219   1.0000
  12.750   1.0813   0.08408   0.07299  -0.0117   0.1184   1.0000
  13.250   1.0757   0.09112   0.08009  -0.0124   0.1127   1.0000
  13.500   1.0734   0.09470   0.08377  -0.0128   0.1101   1.0000
  13.750   1.0722   0.09816   0.08731  -0.0133   0.1082   1.0000
  14.000   1.0716   0.10151   0.09071  -0.0138   0.1066   1.0000
  14.250   1.0719   0.10473   0.09399  -0.0143   0.1050   1.0000
  14.500   1.0740   0.10761   0.09689  -0.0147   0.1037   1.0000
  14.750   1.0720   0.11149   0.10089  -0.0156   0.1026   1.0000
  15.000   1.0675   0.11594   0.10552  -0.0168   0.1018   1.0000
  15.250   1.0575   0.12156   0.11134  -0.0186   0.1006   1.0000
  15.500   1.0425   0.12844   0.11843  -0.0211   0.1000   1.0000
  15.750   1.0041   0.14098   0.13122  -0.0265   0.0990   1.0000
  16.000   0.9539   0.15796   0.14827  -0.0340   0.0982   1.0000
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