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HAM-STD HS1-620 AIRFOIL (hs1620-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-620 AIRFOIL (hs1620-il)
Reynolds number: 50,000
Max Cl/Cd: 16.01 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1620-il-50000.txt
Download as CSV file: xf-hs1620-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HAM-STD HS1-620 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4450   0.13533   0.12833  -0.0052   1.0000   0.3456
  -8.000  -0.3760   0.12931   0.12223  -0.0051   1.0000   0.3557
  -7.750  -0.4266   0.12968   0.12275  -0.0012   1.0000   0.3680
  -7.500  -0.3961   0.12540   0.11847  -0.0003   1.0000   0.3759
  -7.250  -0.4194   0.12468   0.11784   0.0032   1.0000   0.3902
  -7.000  -0.4084   0.12153   0.11473   0.0049   1.0000   0.4000
  -6.750  -0.4521   0.12147   0.11480   0.0100   1.0000   0.4155
  -6.500  -0.4121   0.11777   0.11107   0.0102   1.0000   0.4286
  -6.250  -0.6433   0.08789   0.08062  -0.0110   1.0000   0.2560
  -6.000  -0.6359   0.08408   0.07675  -0.0104   1.0000   0.2532
  -5.750  -0.6311   0.07969   0.07223  -0.0107   1.0000   0.2510
  -5.500  -0.6256   0.07494   0.06724  -0.0118   1.0000   0.2501
  -5.250  -0.6168   0.07050   0.06245  -0.0131   1.0000   0.2510
  -5.000  -0.6044   0.06643   0.05790  -0.0146   1.0000   0.2533
  -4.750  -0.5898   0.06347   0.05467  -0.0151   1.0000   0.2574
  -4.500  -0.5746   0.06222   0.05348  -0.0141   1.0000   0.2624
  -4.250  -0.5577   0.06049   0.05154  -0.0142   1.0000   0.2684
  -4.000  -0.5380   0.05844   0.04900  -0.0152   1.0000   0.2748
  -3.750  -0.5202   0.05696   0.04745  -0.0151   1.0000   0.2811
  -3.500  -0.5023   0.05615   0.04661  -0.0146   1.0000   0.2882
  -3.250  -0.4814   0.05514   0.04524  -0.0151   1.0000   0.2966
  -3.000  -0.4618   0.05418   0.04417  -0.0152   1.0000   0.3041
  -2.750  -0.4428   0.05375   0.04372  -0.0150   1.0000   0.3125
  -2.500  -0.4203   0.05340   0.04296  -0.0156   1.0000   0.3223
  -2.250  -0.4016   0.05293   0.04264  -0.0153   1.0000   0.3308
  -2.000  -0.3809   0.05286   0.04243  -0.0155   1.0000   0.3413
  -1.750  -0.3603   0.05274   0.04226  -0.0156   1.0000   0.3511
  -1.500  -0.3403   0.05290   0.04240  -0.0157   1.0000   0.3623
  -1.250  -0.3194   0.05308   0.04251  -0.0160   1.0000   0.3733
  -1.000  -0.2996   0.05345   0.04289  -0.0161   1.0000   0.3855
  -0.750  -0.2793   0.05387   0.04330  -0.0163   1.0000   0.3978
  -0.500  -0.2598   0.05446   0.04391  -0.0164   1.0000   0.4116
  -0.250  -0.1342   0.05729   0.04678  -0.0344   0.9483   0.4559
   0.000  -0.0620   0.05753   0.04718  -0.0421   0.9147   0.4968
   0.250  -0.0054   0.05762   0.04771  -0.0470   0.8948   0.5539
   0.500   0.0308   0.05700   0.04819  -0.0472   0.8792   0.6984
   0.750   0.0747   0.05675   0.04821  -0.0499   0.8583   1.0000
   1.000   0.1145   0.05731   0.04834  -0.0526   0.8413   1.0000
   1.250   0.1558   0.05780   0.04853  -0.0553   0.8251   1.0000
   1.500   0.2050   0.05811   0.04858  -0.0589   0.8102   1.0000
   1.750   0.2359   0.05842   0.04872  -0.0597   0.7926   1.0000
   2.000   0.2652   0.05878   0.04895  -0.0603   0.7749   1.0000
   2.250   0.2951   0.05911   0.04916  -0.0608   0.7570   1.0000
   2.500   0.3254   0.05941   0.04935  -0.0613   0.7392   1.0000
   2.750   0.3573   0.05966   0.04949  -0.0619   0.7222   1.0000
   3.000   0.4189   0.05853   0.04821  -0.0657   0.7117   1.0000
   3.250   0.4408   0.05894   0.04856  -0.0648   0.6928   1.0000
   3.500   0.4618   0.05953   0.04909  -0.0639   0.6744   1.0000
   3.750   0.4839   0.06013   0.04963  -0.0632   0.6570   1.0000
   4.000   0.5482   0.05795   0.04734  -0.0663   0.6496   1.0000
   4.250   0.5592   0.05921   0.04856  -0.0644   0.6311   1.0000
   4.500   0.5705   0.06063   0.04995  -0.0626   0.6141   1.0000
   4.750   0.6356   0.05774   0.04697  -0.0651   0.6085   1.0000
   5.000   0.6339   0.06030   0.04951  -0.0624   0.5905   1.0000
   5.250   0.7088   0.05621   0.04533  -0.0654   0.5873   1.0000
   5.500   0.6928   0.06017   0.04929  -0.0617   0.5689   1.0000
   5.750   0.7789   0.05509   0.04410  -0.0656   0.5664   1.0000
   6.000   0.7436   0.06081   0.04986  -0.0604   0.5481   1.0000
   6.250   0.8425   0.05475   0.04367  -0.0656   0.5459   1.0000
   6.500   0.7783   0.06321   0.05222  -0.0584   0.5274   1.0000
   6.750   0.8922   0.05573   0.04460  -0.0645   0.5257   1.0000
   7.000   0.7853   0.06888   0.05789  -0.0553   0.5066   1.0000
   7.250   0.9024   0.06022   0.04910  -0.0602   0.5053   1.0000
   7.500   0.7588   0.07923   0.06831  -0.0523   0.4858   1.0000
   7.750   0.6452   0.09603   0.08524  -0.0499   0.4753   1.0000
   8.000   0.6678   0.09746   0.08666  -0.0498   0.4688   1.0000
   8.250   0.6813   0.10007   0.08927  -0.0497   0.4632   1.0000
   8.500   0.6433   0.10836   0.09762  -0.0496   0.4606   1.0000
   8.750   0.6268   0.11422   0.10353  -0.0499   0.4591   1.0000
   9.000   0.6192   0.11942   0.10876  -0.0505   0.4597   1.0000
   9.250   0.6196   0.12416   0.11354  -0.0514   0.4618   1.0000
   9.500   0.6307   0.12841   0.11782  -0.0525   0.4639   1.0000
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