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GOE 474 AIRFOIL (goe474-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 474 AIRFOIL (goe474-il)
Reynolds number: 100,000
Max Cl/Cd: 56.97 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe474-il-100000.txt
Download as CSV file: xf-goe474-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 474 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4237   0.09142   0.08648  -0.0245   1.0000   0.1047
  -7.750  -0.4359   0.08947   0.08465  -0.0259   1.0000   0.1075
  -7.500  -0.4560   0.08805   0.08334  -0.0341   1.0000   0.1091
  -7.250  -0.4514   0.08311   0.07844  -0.0327   1.0000   0.1103
  -7.000  -0.4410   0.07940   0.07478  -0.0288   1.0000   0.1120
  -6.750  -0.4361   0.07643   0.07184  -0.0276   1.0000   0.1145
  -6.500  -0.4343   0.07350   0.06893  -0.0280   1.0000   0.1177
  -6.250  -0.4416   0.07106   0.06625  -0.0370   1.0000   0.1236
  -6.000  -0.4351   0.06654   0.06191  -0.0326   1.0000   0.1251
  -5.750  -0.4292   0.06402   0.05946  -0.0290   1.0000   0.1287
  -5.500  -0.4235   0.06163   0.05664  -0.0346   1.0000   0.1380
  -5.250  -0.4175   0.05735   0.05254  -0.0316   1.0000   0.1395
  -5.000  -0.4010   0.04293   0.03709  -0.0375   1.0000   0.0832
  -4.750  -0.3877   0.03984   0.03395  -0.0361   1.0000   0.0800
  -4.500  -0.3725   0.03514   0.02884  -0.0356   1.0000   0.0766
  -4.250  -0.3543   0.03119   0.02433  -0.0349   1.0000   0.0779
  -4.000  -0.3338   0.02772   0.02020  -0.0341   1.0000   0.0802
  -3.750  -0.3110   0.02477   0.01650  -0.0331   1.0000   0.0823
  -3.500  -0.2909   0.02383   0.01556  -0.0321   1.0000   0.0881
  -3.250  -0.2677   0.02249   0.01368  -0.0310   1.0000   0.0958
  -3.000  -0.2465   0.02159   0.01281  -0.0301   1.0000   0.1031
  -2.750  -0.2254   0.02100   0.01209  -0.0290   1.0000   0.1154
  -2.500  -0.2037   0.02028   0.01126  -0.0280   1.0000   0.1321
  -2.250  -0.1829   0.01973   0.01063  -0.0269   1.0000   0.1622
  -2.000  -0.1631   0.01945   0.01033  -0.0259   1.0000   0.1887
  -1.750  -0.1428   0.01920   0.01001  -0.0250   1.0000   0.2057
  -1.500  -0.1229   0.01913   0.00986  -0.0241   1.0000   0.2241
  -1.250  -0.1033   0.01895   0.00976  -0.0233   1.0000   0.2431
  -1.000  -0.0823   0.01881   0.00956  -0.0225   0.9999   0.2547
  -0.750  -0.0446   0.01875   0.00951  -0.0249   0.9946   0.2672
  -0.500  -0.0095   0.01863   0.00945  -0.0269   0.9889   0.2815
  -0.250   0.0282   0.01859   0.00954  -0.0292   0.9839   0.2992
   0.000   0.0615   0.01848   0.00960  -0.0308   0.9776   0.3273
   0.250   0.1199   0.01661   0.00969  -0.0368   0.9759   1.0000
   0.500   0.1651   0.01707   0.00984  -0.0404   0.9665   1.0000
   0.750   0.2177   0.01746   0.01006  -0.0454   0.9562   1.0000
   1.000   0.2572   0.01767   0.01018  -0.0479   0.9446   1.0000
   1.250   0.2934   0.01794   0.01038  -0.0498   0.9347   1.0000
   1.500   0.3393   0.01817   0.01059  -0.0534   0.9268   1.0000
   1.750   0.3762   0.01833   0.01076  -0.0552   0.9161   1.0000
   2.000   0.4156   0.01840   0.01085  -0.0572   0.9044   1.0000
   2.250   0.4732   0.01793   0.01045  -0.0619   0.8895   1.0000
   2.500   0.5312   0.01724   0.00988  -0.0662   0.8750   1.0000
   2.750   0.5727   0.01688   0.00961  -0.0678   0.8620   1.0000
   3.000   0.6130   0.01638   0.00925  -0.0688   0.8470   1.0000
   3.250   0.6530   0.01567   0.00864  -0.0692   0.8289   1.0000
   3.500   0.6822   0.01518   0.00823  -0.0678   0.8062   1.0000
   3.750   0.7123   0.01467   0.00779  -0.0664   0.7821   1.0000
   4.000   0.7371   0.01435   0.00756  -0.0643   0.7529   1.0000
   4.250   0.7597   0.01413   0.00738  -0.0619   0.7164   1.0000
   4.500   0.7822   0.01396   0.00718  -0.0594   0.6665   1.0000
   4.750   0.8004   0.01405   0.00703  -0.0561   0.5784   1.0000
   5.000   0.8110   0.01499   0.00710  -0.0519   0.4333   1.0000
   5.250   0.8226   0.01643   0.00785  -0.0488   0.3454   1.0000
   5.500   0.8391   0.01766   0.00866  -0.0467   0.2950   1.0000
   5.750   0.8587   0.01872   0.00951  -0.0452   0.2604   1.0000
   6.000   0.8792   0.01974   0.01035  -0.0439   0.2346   1.0000
   6.250   0.9000   0.02067   0.01123  -0.0427   0.2119   1.0000
   6.500   0.9212   0.02170   0.01218  -0.0416   0.1921   1.0000
   6.750   0.9417   0.02265   0.01316  -0.0404   0.1720   1.0000
   7.000   0.9611   0.02378   0.01418  -0.0391   0.1512   1.0000
   7.250   0.9781   0.02471   0.01518  -0.0374   0.1272   1.0000
   7.500   0.9955   0.02608   0.01662  -0.0356   0.1043   1.0000
   7.750   1.0132   0.02747   0.01794  -0.0341   0.0870   1.0000
   8.000   1.0344   0.02950   0.02010  -0.0328   0.0756   1.0000
   8.250   1.0548   0.03160   0.02234  -0.0315   0.0674   1.0000
   8.500   1.0745   0.03335   0.02420  -0.0303   0.0615   1.0000
   8.750   1.0943   0.03668   0.02779  -0.0291   0.0584   1.0000
   9.000   1.1081   0.03960   0.03131  -0.0268   0.0559   1.0000
   9.250   1.1201   0.04215   0.03423  -0.0247   0.0529   1.0000
   9.500   1.1333   0.04438   0.03660  -0.0232   0.0502   1.0000
   9.750   1.1404   0.04800   0.04055  -0.0210   0.0494   1.0000
  10.000   1.1416   0.05215   0.04510  -0.0185   0.0491   1.0000
  10.250   1.1361   0.05623   0.04965  -0.0154   0.0494   1.0000
  10.500   1.1108   0.06120   0.05524  -0.0110   0.0507   1.0000
  10.750   1.0749   0.06614   0.06061  -0.0068   0.0521   1.0000
  11.000   1.0435   0.07112   0.06584  -0.0049   0.0531   1.0000
  11.250   1.0126   0.07686   0.07177  -0.0055   0.0542   1.0000
  11.500   0.9825   0.08361   0.07865  -0.0083   0.0551   1.0000
  11.750   0.9523   0.09213   0.08726  -0.0135   0.0562   1.0000
  12.000   0.9324   0.10064   0.09577  -0.0187   0.0576   1.0000
  12.250   0.9206   0.10842   0.10353  -0.0226   0.0587   1.0000
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