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HAM-STD HS1-606 AIRFOIL (hs1606-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HAM-STD HS1-606 AIRFOIL (hs1606-il)
Reynolds number: 50,000
Max Cl/Cd: 45.02 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hs1606-il-50000-n5.txt
Download as CSV file: xf-hs1606-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-606 AIRFOIL                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3644   0.09586   0.08929  -0.0283   1.0000   0.0505
  -7.000  -0.3674   0.09310   0.08663  -0.0284   1.0000   0.0470
  -6.750  -0.3707   0.09012   0.08372  -0.0311   1.0000   0.0418
  -6.500  -0.3695   0.08738   0.08103  -0.0302   1.0000   0.0407
  -6.250  -0.3677   0.08454   0.07825  -0.0303   1.0000   0.0398
  -6.000  -0.3639   0.08149   0.07524  -0.0312   1.0000   0.0388
  -5.750  -0.3574   0.07817   0.07194  -0.0329   1.0000   0.0379
  -5.500  -0.3475   0.07451   0.06827  -0.0354   1.0000   0.0370
  -5.250  -0.3335   0.07046   0.06419  -0.0389   1.0000   0.0362
  -5.000  -0.3149   0.06607   0.05974  -0.0431   1.0000   0.0356
  -4.750  -0.2921   0.06161   0.05518  -0.0477   1.0000   0.0358
  -4.500  -0.2651   0.05704   0.05046  -0.0528   1.0000   0.0367
  -4.250  -0.2322   0.05198   0.04517  -0.0588   1.0000   0.0381
  -4.000  -0.1919   0.04606   0.03888  -0.0660   1.0000   0.0394
  -3.750  -0.1430   0.03909   0.03123  -0.0742   1.0000   0.0407
  -3.500  -0.0896   0.03237   0.02331  -0.0817   1.0000   0.0426
  -3.250  -0.0573   0.03039   0.02106  -0.0836   1.0000   0.0483
  -3.000  -0.0233   0.02847   0.01860  -0.0853   1.0000   0.0619
  -2.750   0.0066   0.02765   0.01747  -0.0861   1.0000   0.0938
  -2.500   0.0302   0.02791   0.01770  -0.0858   1.0000   0.1265
  -2.250   0.0578   0.02745   0.01685  -0.0861   1.0000   0.1480
  -2.000   0.0894   0.02679   0.01584  -0.0871   0.9985   0.1619
  -1.750   0.1246   0.02646   0.01524  -0.0890   0.9951   0.1804
  -1.500   0.1592   0.02605   0.01453  -0.0905   0.9914   0.1957
  -1.250   0.1942   0.02585   0.01407  -0.0922   0.9872   0.2179
  -1.000   0.2311   0.02560   0.01368  -0.0943   0.9836   0.2387
  -0.750   0.2642   0.02541   0.01334  -0.0957   0.9784   0.2625
  -0.500   0.2996   0.02524   0.01313  -0.0976   0.9735   0.2888
  -0.250   0.3370   0.02506   0.01301  -0.0999   0.9693   0.3187
   0.000   0.3691   0.02488   0.01298  -0.1013   0.9630   0.3536
   0.250   0.4069   0.02439   0.01304  -0.1039   0.9586   0.4499
   0.500   0.4278   0.02356   0.01303  -0.1024   0.9496   1.0000
   0.750   0.4655   0.02395   0.01317  -0.1046   0.9436   1.0000
   1.000   0.4956   0.02432   0.01339  -0.1053   0.9349   1.0000
   1.250   0.5317   0.02464   0.01360  -0.1072   0.9269   1.0000
   1.500   0.5718   0.02482   0.01371  -0.1095   0.9168   1.0000
   1.750   0.6089   0.02490   0.01378  -0.1111   0.9042   1.0000
   2.000   0.6445   0.02497   0.01389  -0.1123   0.8913   1.0000
   2.250   0.6777   0.02508   0.01405  -0.1131   0.8791   1.0000
   2.500   0.7101   0.02521   0.01425  -0.1137   0.8672   1.0000
   2.750   0.7424   0.02529   0.01443  -0.1142   0.8553   1.0000
   3.000   0.7747   0.02533   0.01467  -0.1146   0.8429   1.0000
   3.250   0.8063   0.02532   0.01482  -0.1147   0.8297   1.0000
   3.500   0.8366   0.02528   0.01496  -0.1145   0.8150   1.0000
   3.750   0.8662   0.02520   0.01507  -0.1140   0.7990   1.0000
   4.000   0.8964   0.02501   0.01518  -0.1134   0.7820   1.0000
   4.250   0.9245   0.02483   0.01524  -0.1124   0.7625   1.0000
   4.500   0.9503   0.02467   0.01534  -0.1109   0.7396   1.0000
   4.750   0.9744   0.02454   0.01548  -0.1091   0.7129   1.0000
   5.000   0.9990   0.02431   0.01551  -0.1072   0.6806   1.0000
   5.250   1.0226   0.02364   0.01496  -0.1041   0.6188   1.0000
   5.500   1.0475   0.02327   0.01380  -0.1003   0.4963   1.0000
   5.750   1.0601   0.02443   0.01436  -0.0970   0.3974   1.0000
   6.000   1.0713   0.02586   0.01538  -0.0941   0.3183   1.0000
   6.250   1.0798   0.02770   0.01670  -0.0913   0.2102   1.0000
   6.500   1.0873   0.03020   0.01839  -0.0888   0.1260   1.0000
   6.750   1.1007   0.03222   0.02025  -0.0869   0.1005   1.0000
   7.000   1.1158   0.03405   0.02212  -0.0850   0.0896   1.0000
   7.250   1.1338   0.03575   0.02402  -0.0833   0.0822   1.0000
   7.500   1.1517   0.03768   0.02597  -0.0818   0.0756   1.0000
   7.750   1.1724   0.03937   0.02793  -0.0806   0.0678   1.0000
   8.000   1.1963   0.04170   0.03023  -0.0799   0.0632   1.0000
   8.250   1.2257   0.04412   0.03308  -0.0794   0.0600   1.0000
   8.500   1.2522   0.04698   0.03632  -0.0787   0.0570   1.0000
   8.750   1.2707   0.04969   0.03934  -0.0777   0.0528   1.0000
   9.000   1.2856   0.05305   0.04306  -0.0763   0.0494   1.0000
   9.250   1.2968   0.05670   0.04733  -0.0740   0.0479   1.0000
   9.500   1.3023   0.06065   0.05184  -0.0715   0.0467   1.0000
   9.750   1.3019   0.06470   0.05640  -0.0686   0.0458   1.0000
  10.000   1.2961   0.06856   0.06069  -0.0656   0.0446   1.0000
  10.250   1.2870   0.07212   0.06459  -0.0626   0.0433   1.0000
  10.500   1.2763   0.07536   0.06804  -0.0596   0.0419   1.0000
  10.750   1.2688   0.07867   0.07146  -0.0575   0.0403   1.0000
  11.000   1.2562   0.08282   0.07576  -0.0557   0.0394   1.0000
  11.250   1.2386   0.08741   0.08056  -0.0545   0.0391   1.0000
  11.500   1.2177   0.09222   0.08562  -0.0541   0.0392   1.0000
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