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GOE 424 AIRFOIL (goe424-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 424 AIRFOIL (goe424-il)
Reynolds number: 100,000
Max Cl/Cd: 22.45 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe424-il-100000.txt
Download as CSV file: xf-goe424-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 424 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.2549   0.13729   0.13271  -0.0461   1.0000   0.1303
 -12.250  -0.2642   0.13578   0.13128  -0.0450   1.0000   0.1355
 -12.000  -0.3287   0.13535   0.13106  -0.0471   1.0000   0.1388
 -11.750  -0.2914   0.13244   0.12818  -0.0415   1.0000   0.1419
 -11.500  -0.2768   0.12996   0.12573  -0.0428   0.9971   0.1497
 -11.250  -0.2629   0.12464   0.12040  -0.0489   0.9924   0.1574
 -11.000  -0.2915   0.12014   0.11597  -0.0608   0.9836   0.1691
 -10.750  -0.2157   0.11521   0.11094  -0.0594   0.9815   0.1748
 -10.500  -0.2288   0.10981   0.10560  -0.0683   0.9717   0.1864
 -10.250  -0.1704   0.10597   0.10166  -0.0701   0.9684   0.1961
 -10.000  -0.1583   0.10082   0.09653  -0.0758   0.9584   0.2063
  -9.750  -0.1685   0.09571   0.09146  -0.0841   0.9469   0.2207
  -9.500  -0.1093   0.09165   0.08731  -0.0852   0.9405   0.2266
  -9.250  -0.1119   0.08687   0.08255  -0.0903   0.9248   0.2400
  -9.000  -0.0789   0.08363   0.07924  -0.0913   0.9091   0.2481
  -8.750  -0.3494   0.05157   0.04573  -0.1062   0.8698   0.1227
  -8.500  -0.3516   0.04602   0.03939  -0.1037   0.8562   0.1087
  -8.250  -0.3356   0.04251   0.03560  -0.1028   0.8422   0.1052
  -8.000  -0.3212   0.03970   0.03233  -0.1013   0.8295   0.1033
  -7.750  -0.2981   0.03706   0.02920  -0.1008   0.8209   0.1025
  -7.500  -0.2816   0.03521   0.02692  -0.0990   0.8075   0.1014
  -7.250  -0.2594   0.03350   0.02478  -0.0979   0.7969   0.1006
  -7.000  -0.2315   0.03193   0.02297  -0.0979   0.7877   0.1018
  -6.750  -0.2079   0.03080   0.02167  -0.0971   0.7770   0.1034
  -6.500  -0.1777   0.02949   0.02011  -0.0973   0.7693   0.1045
  -6.250  -0.1532   0.02861   0.01908  -0.0966   0.7597   0.1054
  -6.000  -0.1235   0.02767   0.01797  -0.0967   0.7527   0.1074
  -5.750  -0.0981   0.02712   0.01727  -0.0961   0.7452   0.1097
  -5.500  -0.0708   0.02624   0.01639  -0.0960   0.7381   0.1117
  -5.250  -0.0406   0.02529   0.01547  -0.0962   0.7330   0.1144
  -5.000  -0.0222   0.02496   0.01523  -0.0948   0.7253   0.1174
  -4.750   0.0007   0.02453   0.01475  -0.0939   0.7194   0.1219
  -4.500   0.0252   0.02397   0.01412  -0.0932   0.7151   0.1269
  -4.250   0.0386   0.02388   0.01411  -0.0910   0.7086   0.1321
  -4.000   0.0586   0.02364   0.01385  -0.0898   0.7036   0.1400
  -3.750   0.0806   0.02312   0.01348  -0.0889   0.6996   0.1616
  -3.500   0.0925   0.02223   0.01334  -0.0867   0.6952   0.2846
  -3.250   0.0987   0.02190   0.01387  -0.0831   0.6897   0.4756
  -3.000   0.1168   0.02197   0.01418  -0.0808   0.6852   0.5623
  -2.750   0.1397   0.02212   0.01442  -0.0791   0.6818   0.6214
  -2.500   0.1587   0.02256   0.01493  -0.0771   0.6782   0.6633
  -2.250   0.1713   0.02323   0.01571  -0.0743   0.6732   0.6957
  -2.000   0.1905   0.02365   0.01615  -0.0723   0.6690   0.7284
  -1.750   0.2159   0.02397   0.01647  -0.0709   0.6655   0.7583
  -1.500   0.2440   0.02423   0.01664  -0.0700   0.6628   0.7866
  -1.250   0.2504   0.02531   0.01786  -0.0666   0.6579   0.8077
  -1.000   0.2640   0.02623   0.01883  -0.0639   0.6535   0.8319
  -0.750   0.2878   0.02677   0.01932  -0.0626   0.6500   0.8585
  -0.500   0.3277   0.02713   0.01956  -0.0636   0.6471   0.8817
  -0.250   0.3887   0.02765   0.01989  -0.0681   0.6447   0.9039
   0.000   0.4078   0.02958   0.02196  -0.0684   0.6390   0.9247
   0.250   0.4593   0.03041   0.02271  -0.0737   0.6346   0.9391
   0.500   0.5144   0.03055   0.02270  -0.0792   0.6313   0.9517
   0.750   0.5822   0.03040   0.02235  -0.0869   0.6287   0.9598
   1.000   0.6301   0.03104   0.02293  -0.0920   0.6254   0.9717
   1.250   0.6567   0.03307   0.02509  -0.0954   0.6188   0.9876
   1.500   0.7124   0.03336   0.02531  -0.1020   0.6148   0.9980
   1.750   0.7325   0.03360   0.02547  -0.1019   0.6120   1.0000
   2.000   0.7529   0.03354   0.02529  -0.1011   0.6097   1.0000
   2.250   0.4197   0.04692   0.03911  -0.0566   0.5926   1.0000
   2.500   0.4790   0.04526   0.03731  -0.0592   0.5915   1.0000
   2.750   0.5502   0.04323   0.03514  -0.0635   0.5909   1.0000
   3.000   0.3762   0.05591   0.04800  -0.0480   0.5758   1.0000
   3.250   0.4337   0.05454   0.04649  -0.0498   0.5734   1.0000
   3.500   0.2913   0.07213   0.06444  -0.0472   0.6264   1.0000
   3.750   0.2908   0.07102   0.06325  -0.0433   0.5967   1.0000
   4.000   0.3230   0.07455   0.06673  -0.0460   0.6081   1.0000
   4.250   0.2949   0.07612   0.06832  -0.0423   0.5974   1.0000
   4.500   0.4141   0.06760   0.05946  -0.0424   0.5424   1.0000
   4.750   0.4711   0.06618   0.05792  -0.0436   0.5384   1.0000
   5.000   0.4354   0.07090   0.06270  -0.0411   0.5285   1.0000
   5.250   0.4703   0.07084   0.06256  -0.0413   0.5228   1.0000
   5.500   0.4814   0.07247   0.06417  -0.0406   0.5153   1.0000
   5.750   0.4865   0.07442   0.06611  -0.0398   0.5074   1.0000
   6.000   0.5347   0.07335   0.06497  -0.0404   0.5036   1.0000
   6.250   0.5111   0.07744   0.06910  -0.0387   0.4922   1.0000
   6.500   0.5483   0.07707   0.06868  -0.0388   0.4875   1.0000
   6.750   0.5413   0.08012   0.07175  -0.0378   0.4779   1.0000
   7.000   0.5634   0.08090   0.07251  -0.0376   0.4720   1.0000
   7.250   0.6076   0.07990   0.07149  -0.0378   0.4691   1.0000
   7.500   0.5851   0.08418   0.07580  -0.0366   0.4565   1.0000
   7.750   0.6238   0.08351   0.07510  -0.0366   0.4532   1.0000
   8.000   0.6686   0.08234   0.07392  -0.0367   0.4513   1.0000
   8.250   0.6343   0.08798   0.07961  -0.0357   0.4378   1.0000
   8.500   0.6595   0.08848   0.08011  -0.0354   0.4330   1.0000
   8.750   0.6504   0.09193   0.08360  -0.0349   0.4226   1.0000
   9.000   0.6895   0.09097   0.08263  -0.0348   0.4200   1.0000
   9.250   0.6610   0.09677   0.08848  -0.0345   0.4082   1.0000
   9.500   0.6925   0.09659   0.08831  -0.0343   0.4051   1.0000
   9.750   0.7326   0.09545   0.08717  -0.0340   0.4033   1.0000
  10.000   0.6972   0.10213   0.09391  -0.0340   0.3906   1.0000
  10.250   0.7357   0.10100   0.09279  -0.0337   0.3883   1.0000
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