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GOE 384 AIRFOIL (goe384-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 384 AIRFOIL (goe384-il)
Reynolds number: 100,000
Max Cl/Cd: 39.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe384-il-100000-n5.txt
Download as CSV file: xf-goe384-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 384 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0111   0.10996   0.10431  -0.0930   0.7957   0.0879
 -10.500   0.0096   0.10675   0.10106  -0.0952   0.7882   0.0883
 -10.000   0.0111   0.09670   0.09091  -0.0993   0.7749   0.0723
  -9.750   0.0218   0.09426   0.08844  -0.0996   0.7678   0.0728
  -9.250   0.0094   0.08343   0.07751  -0.1062   0.7566   0.0647
  -9.000   0.0165   0.08065   0.07471  -0.1072   0.7505   0.0644
  -8.750   0.0197   0.07728   0.07133  -0.1090   0.7444   0.0639
  -8.500   0.0190   0.07327   0.06728  -0.1114   0.7394   0.0635
  -8.250   0.0113   0.06820   0.06218  -0.1157   0.7341   0.0631
  -8.000  -0.0072   0.06173   0.05561  -0.1214   0.7285   0.0630
  -7.750  -0.0231   0.05544   0.04904  -0.1249   0.7241   0.0632
  -7.500  -0.0309   0.05031   0.04353  -0.1262   0.7205   0.0635
  -7.250  -0.0317   0.04629   0.03915  -0.1264   0.7155   0.0637
  -7.000  -0.0274   0.04276   0.03519  -0.1259   0.7101   0.0640
  -6.750  -0.0187   0.03945   0.03132  -0.1252   0.7055   0.0645
  -6.500  -0.0008   0.03762   0.02920  -0.1246   0.7007   0.0653
  -6.250   0.0192   0.03678   0.02832  -0.1241   0.6939   0.0663
  -6.000   0.0403   0.03557   0.02691  -0.1236   0.6884   0.0675
  -5.500   0.0815   0.03265   0.02335  -0.1224   0.6788   0.0698
  -5.250   0.1031   0.03128   0.02163  -0.1218   0.6742   0.0708
  -5.000   0.1271   0.03002   0.01998  -0.1214   0.6703   0.0722
  -4.750   0.1540   0.02935   0.01924  -0.1215   0.6668   0.0737
  -4.500   0.1775   0.02884   0.01866  -0.1210   0.6623   0.0753
  -4.250   0.2014   0.02820   0.01787  -0.1206   0.6575   0.0771
  -4.000   0.2275   0.02744   0.01687  -0.1203   0.6533   0.0787
  -3.750   0.2554   0.02673   0.01596  -0.1203   0.6496   0.0805
  -3.500   0.2816   0.02634   0.01555  -0.1202   0.6455   0.0826
  -3.250   0.3047   0.02605   0.01523  -0.1195   0.6402   0.0851
  -3.000   0.3307   0.02563   0.01468  -0.1192   0.6356   0.0876
  -2.750   0.3586   0.02514   0.01411  -0.1192   0.6315   0.0898
  -2.500   0.3872   0.02477   0.01369  -0.1194   0.6279   0.0929
  -2.250   0.4082   0.02466   0.01361  -0.1184   0.6221   0.0964
  -2.000   0.4327   0.02439   0.01332  -0.1178   0.6169   0.0998
  -1.750   0.4599   0.02404   0.01296  -0.1177   0.6123   0.1035
  -1.500   0.4884   0.02379   0.01259  -0.1178   0.6083   0.1090
  -1.250   0.5070   0.02371   0.01266  -0.1165   0.6022   0.1140
  -1.000   0.5310   0.02357   0.01250  -0.1159   0.5968   0.1207
  -0.750   0.5584   0.02328   0.01218  -0.1159   0.5922   0.1297
  -0.500   0.5829   0.02312   0.01206  -0.1154   0.5871   0.1422
  -0.250   0.6022   0.02310   0.01219  -0.1142   0.5803   0.1598
   0.000   0.6274   0.02275   0.01209  -0.1140   0.5749   0.2205
   0.250   0.6546   0.02197   0.01197  -0.1142   0.5708   0.4325
   0.500   0.6636   0.02162   0.01253  -0.1108   0.5636   0.6514
   0.750   0.7309   0.02130   0.01272  -0.1172   0.5569   0.9918
   1.000   0.7614   0.02134   0.01253  -0.1178   0.5521   1.0000
   1.250   0.7699   0.02175   0.01293  -0.1148   0.5441   1.0000
   1.500   0.7903   0.02187   0.01291  -0.1136   0.5383   1.0000
   1.750   0.8089   0.02209   0.01301  -0.1121   0.5324   1.0000
   2.000   0.8223   0.02246   0.01333  -0.1099   0.5252   1.0000
   2.250   0.8447   0.02257   0.01330  -0.1091   0.5201   1.0000
   2.500   0.8586   0.02297   0.01365  -0.1071   0.5133   1.0000
   2.750   0.8750   0.02328   0.01388  -0.1054   0.5068   1.0000
   3.000   0.8994   0.02334   0.01379  -0.1049   0.5023   1.0000
   3.250   0.9078   0.02394   0.01438  -0.1021   0.4950   1.0000
   3.500   0.9252   0.02422   0.01458  -0.1006   0.4896   1.0000
   3.750   0.9501   0.02433   0.01453  -0.1002   0.4857   1.0000
   4.000   0.9581   0.02506   0.01527  -0.0976   0.4794   1.0000
   4.250   0.9759   0.02546   0.01560  -0.0963   0.4744   1.0000
   4.500   1.0010   0.02560   0.01560  -0.0961   0.4705   1.0000
   4.750   1.0140   0.02628   0.01626  -0.0943   0.4652   1.0000
   5.000   1.0292   0.02690   0.01685  -0.0929   0.4601   1.0000
   5.250   1.0513   0.02724   0.01709  -0.0924   0.4562   1.0000
   5.500   1.0805   0.02733   0.01704  -0.0927   0.4531   1.0000
   5.750   1.0885   0.02838   0.01815  -0.0907   0.4483   1.0000
   6.000   1.1032   0.02915   0.01890  -0.0894   0.4440   1.0000
   6.250   1.1246   0.02961   0.01929  -0.0889   0.4403   1.0000
   6.500   1.1529   0.02976   0.01934  -0.0892   0.4372   1.0000
   6.750   1.1669   0.03063   0.02022  -0.0880   0.4333   1.0000
   7.000   1.1749   0.03182   0.02146  -0.0862   0.4290   1.0000
   7.250   1.1914   0.03261   0.02225  -0.0853   0.4255   1.0000
   7.500   1.2143   0.03308   0.02268  -0.0851   0.4226   1.0000
   7.750   1.2430   0.03327   0.02280  -0.0855   0.4201   1.0000
   8.000   1.2595   0.03413   0.02367  -0.0847   0.4170   1.0000
   8.250   1.2550   0.03612   0.02580  -0.0820   0.4126   1.0000
   8.500   1.2637   0.03745   0.02717  -0.0806   0.4089   1.0000
   8.750   1.2827   0.03815   0.02787  -0.0801   0.4058   1.0000
   9.000   1.3094   0.03844   0.02812  -0.0803   0.4034   1.0000
   9.250   1.3418   0.03846   0.02808  -0.0810   0.4015   1.0000
   9.500   1.3205   0.04175   0.03158  -0.0774   0.3973   1.0000
   9.750   1.2953   0.04569   0.03572  -0.0740   0.3923   1.0000
  10.000   1.3028   0.04734   0.03741  -0.0730   0.3888   1.0000
  10.250   1.3270   0.04767   0.03774  -0.0729   0.3864   1.0000
  10.500   1.3590   0.04745   0.03748  -0.0734   0.3846   1.0000
  10.750   1.3950   0.04705   0.03704  -0.0742   0.3831   1.0000
  11.000   1.2174   0.06615   0.05674  -0.0658   0.3680   1.0000
  11.250   1.2500   0.06532   0.05590  -0.0659   0.3670   1.0000
  11.500   1.2862   0.06416   0.05471  -0.0660   0.3661   1.0000
  11.750   1.3245   0.06287   0.05341  -0.0663   0.3653   1.0000
  12.250   1.0820   0.09969   0.09078  -0.0638   0.3307   1.0000
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