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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 500,000
Max Cl/Cd: 114.73 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1404-il-500000.txt
Download as CSV file: xf-hs1404-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4470   0.09829   0.09601  -0.0089   1.0000   0.0077
  -7.750  -0.4402   0.09530   0.09304  -0.0107   1.0000   0.0078
  -7.500  -0.4342   0.09226   0.09003  -0.0124   1.0000   0.0079
  -5.250  -0.3305   0.05537   0.05315  -0.0416   0.9998   0.0088
  -5.000  -0.2940   0.05010   0.04779  -0.0492   0.9977   0.0097
  -4.750  -0.2551   0.04547   0.04306  -0.0561   0.9958   0.0107
  -4.500  -0.2124   0.04031   0.03774  -0.0632   0.9942   0.0120
  -4.250  -0.1695   0.03489   0.03211  -0.0695   0.9918   0.0136
  -4.000  -0.1252   0.02906   0.02596  -0.0748   0.9897   0.0156
  -3.750  -0.0820   0.02607   0.02260  -0.0774   0.9877   0.0183
  -3.500  -0.0428   0.01890   0.01480  -0.0826   0.9864   0.0217
  -3.250  -0.0026   0.01493   0.01020  -0.0843   0.9852   0.0147
  -2.750   0.0711   0.01175   0.00641  -0.0877   0.9828   0.0167
  -2.500   0.1058   0.01017   0.00455  -0.0888   0.9805   0.0149
  -2.250   0.1403   0.00914   0.00337  -0.0900   0.9776   0.0138
  -2.000   0.1753   0.00849   0.00259  -0.0913   0.9746   0.0135
  -1.750   0.2111   0.00808   0.00204  -0.0927   0.9715   0.0147
  -1.500   0.2443   0.00736   0.00174  -0.0939   0.9659   0.1498
  -1.250   0.2754   0.00714   0.00172  -0.0946   0.9578   0.2222
  -1.000   0.3035   0.00704   0.00151  -0.0944   0.9476   0.2280
  -0.750   0.3307   0.00683   0.00147  -0.0942   0.9381   0.2809
  -0.500   0.3573   0.00655   0.00140  -0.0939   0.9284   0.3568
  -0.250   0.3762   0.00499   0.00140  -0.0918   0.9182   1.0000
   0.000   0.4031   0.00503   0.00137  -0.0914   0.9093   1.0000
   0.250   0.4300   0.00509   0.00135  -0.0910   0.9015   1.0000
   0.500   0.4570   0.00514   0.00138  -0.0907   0.8930   1.0000
   0.750   0.4840   0.00519   0.00140  -0.0904   0.8841   1.0000
   1.000   0.5108   0.00526   0.00142  -0.0900   0.8753   1.0000
   1.250   0.5376   0.00532   0.00146  -0.0897   0.8653   1.0000
   1.500   0.5642   0.00538   0.00150  -0.0892   0.8525   1.0000
   1.750   0.5898   0.00545   0.00151  -0.0884   0.8308   1.0000
   2.000   0.6155   0.00553   0.00154  -0.0877   0.8058   1.0000
   2.250   0.6408   0.00566   0.00161  -0.0868   0.7699   1.0000
   2.500   0.6666   0.00581   0.00166  -0.0862   0.7278   1.0000
   2.750   0.6911   0.00614   0.00173  -0.0853   0.6502   1.0000
   3.000   0.7123   0.00711   0.00201  -0.0841   0.4968   1.0000
   3.250   0.7336   0.00831   0.00244  -0.0834   0.3270   1.0000
   3.500   0.7557   0.00948   0.00291  -0.0829   0.1703   1.0000
   3.750   0.7780   0.01071   0.00358  -0.0823   0.0564   1.0000
   4.000   0.8031   0.01140   0.00432  -0.0817   0.0380   1.0000
   4.250   0.8285   0.01201   0.00500  -0.0812   0.0293   1.0000
   4.500   0.8528   0.01285   0.00592  -0.0805   0.0246   1.0000
   4.750   0.8800   0.01281   0.00587  -0.0806   0.0179   1.0000
   5.000   0.9055   0.01330   0.00633  -0.0802   0.0080   1.0000
   5.250   0.9252   0.01557   0.00886  -0.0782   0.0045   1.0000
   5.500   0.9470   0.01753   0.01108  -0.0766   0.0040   1.0000
   5.750   0.9687   0.02039   0.01429  -0.0749   0.0039   1.0000
   6.000   0.9895   0.02430   0.01869  -0.0728   0.0041   1.0000
   6.250   1.0054   0.02979   0.02481  -0.0701   0.0044   1.0000
   6.500   0.9845   0.02081   0.01642  -0.0623   0.0053   1.0000
   6.750   1.0094   0.04948   0.04581  -0.0623   0.0118   1.0000
   7.000   1.0163   0.05415   0.05077  -0.0604   0.0118   1.0000
   7.250   1.0207   0.05882   0.05571  -0.0585   0.0117   1.0000
   7.500   1.0223   0.06349   0.06062  -0.0569   0.0117   1.0000
   7.750   1.0210   0.06813   0.06548  -0.0554   0.0117   1.0000
   8.000   1.0164   0.07275   0.07028  -0.0542   0.0117   1.0000
   8.250   1.0083   0.07731   0.07499  -0.0534   0.0116   1.0000
   8.500   0.9935   0.08137   0.07917  -0.0523   0.0116   1.0000
   8.750   0.9779   0.08618   0.08408  -0.0533   0.0116   1.0000
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