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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 200,000
Max Cl/Cd: 78.6 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1404-il-200000-n5.txt
Download as CSV file: xf-hs1404-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-404 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.4454   0.09557   0.09204  -0.0097   1.0000   0.0135
  -7.500  -0.4404   0.09242   0.08893  -0.0112   1.0000   0.0138
  -7.250  -0.4353   0.08927   0.08582  -0.0129   1.0000   0.0141
  -7.000  -0.4268   0.08580   0.08238  -0.0157   1.0000   0.0143
  -6.750  -0.4167   0.08221   0.07883  -0.0189   1.0000   0.0146
  -6.500  -0.4054   0.07851   0.07515  -0.0224   1.0000   0.0148
  -5.000  -0.3007   0.05267   0.04910  -0.0457   1.0000   0.0074
  -4.750  -0.2737   0.04754   0.04385  -0.0506   0.9993   0.0071
  -4.500  -0.2297   0.04110   0.03718  -0.0586   0.9965   0.0070
  -4.250  -0.1845   0.03449   0.03025  -0.0655   0.9943   0.0069
  -4.000  -0.1415   0.02812   0.02343  -0.0705   0.9918   0.0073
  -3.750  -0.1019   0.02306   0.01773  -0.0750   0.9893   0.0107
  -3.500  -0.0647   0.02013   0.01428  -0.0775   0.9868   0.0123
  -3.250  -0.0271   0.01716   0.01063  -0.0793   0.9848   0.0117
  -3.000   0.0088   0.01519   0.00821  -0.0807   0.9831   0.0114
  -2.750   0.0425   0.01378   0.00653  -0.0817   0.9803   0.0112
  -2.500   0.0758   0.01275   0.00531  -0.0827   0.9768   0.0113
  -2.250   0.1103   0.01201   0.00433  -0.0840   0.9738   0.0120
  -2.000   0.1451   0.01147   0.00359  -0.0854   0.9712   0.0136
  -1.750   0.1792   0.01079   0.00302  -0.0867   0.9682   0.0612
  -1.500   0.2103   0.01033   0.00308  -0.0878   0.9632   0.1947
  -1.250   0.2432   0.01019   0.00292  -0.0890   0.9591   0.2220
  -1.000   0.2763   0.01002   0.00276  -0.0902   0.9554   0.2492
  -0.750   0.3070   0.00984   0.00258  -0.0909   0.9485   0.2790
  -0.250   0.3632   0.00793   0.00238  -0.0906   0.9325   1.0000
   0.000   0.3933   0.00792   0.00228  -0.0908   0.9216   1.0000
   0.250   0.4226   0.00791   0.00219  -0.0908   0.9094   1.0000
   0.500   0.4508   0.00792   0.00217  -0.0906   0.8969   1.0000
   0.750   0.4786   0.00796   0.00216  -0.0903   0.8862   1.0000
   1.250   0.5334   0.00807   0.00225  -0.0898   0.8668   1.0000
   1.500   0.5603   0.00814   0.00233  -0.0894   0.8558   1.0000
   1.750   0.5871   0.00822   0.00243  -0.0890   0.8438   1.0000
   2.000   0.6137   0.00830   0.00254  -0.0885   0.8300   1.0000
   2.250   0.6393   0.00837   0.00271  -0.0876   0.8078   1.0000
   2.500   0.6631   0.00847   0.00271  -0.0861   0.7623   1.0000
   2.750   0.6854   0.00872   0.00267  -0.0842   0.6691   1.0000
   3.000   0.7027   0.00979   0.00281  -0.0818   0.4883   1.0000
   3.250   0.7227   0.01096   0.00328  -0.0806   0.3418   1.0000
   3.500   0.7454   0.01187   0.00377  -0.0800   0.2372   1.0000
   3.750   0.7656   0.01336   0.00448  -0.0793   0.0866   1.0000
   4.000   0.7894   0.01423   0.00531  -0.0788   0.0506   1.0000
   4.250   0.8143   0.01490   0.00606  -0.0782   0.0394   1.0000
   4.500   0.8381   0.01581   0.00708  -0.0774   0.0325   1.0000
   4.750   0.8625   0.01651   0.00790  -0.0768   0.0257   1.0000
   5.000   0.8847   0.01780   0.00931  -0.0758   0.0214   1.0000
   5.250   0.9096   0.01843   0.01006  -0.0752   0.0141   1.0000
   5.750   0.9550   0.02093   0.01279  -0.0734   0.0050   1.0000
   6.000   0.9768   0.02304   0.01518  -0.0720   0.0041   1.0000
   6.250   0.9984   0.02599   0.01867  -0.0704   0.0035   1.0000
   6.500   1.0186   0.02969   0.02293  -0.0685   0.0032   1.0000
   6.750   1.0357   0.03420   0.02807  -0.0662   0.0031   1.0000
   7.000   1.0485   0.03941   0.03391  -0.0636   0.0031   1.0000
   7.250   1.0573   0.04501   0.04005  -0.0610   0.0032   1.0000
   7.500   1.0624   0.05065   0.04615  -0.0586   0.0032   1.0000
   7.750   1.0641   0.05623   0.05211  -0.0565   0.0033   1.0000
   8.000   1.0620   0.06174   0.05794  -0.0547   0.0033   1.0000
   8.250   1.0562   0.06711   0.06356  -0.0533   0.0034   1.0000
   8.500   1.0465   0.07234   0.06899  -0.0524   0.0034   1.0000
   8.750   1.0313   0.07708   0.07389  -0.0515   0.0035   1.0000
   9.000   1.0149   0.08237   0.07929  -0.0527   0.0035   1.0000
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