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HAM-STD HS1-404 AIRFOIL (hs1404-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HAM-STD HS1-404 AIRFOIL (hs1404-il)
Reynolds number: 50,000
Max Cl/Cd: 42.11 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hs1404-il-50000.txt
Download as CSV file: xf-hs1404-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4658   0.11061   0.10377  -0.0062   1.0000   0.1287
  -8.000  -0.4672   0.10911   0.10236  -0.0086   1.0000   0.1330
  -7.750  -0.4698   0.10794   0.10133  -0.0129   1.0000   0.1347
  -7.500  -0.4530   0.10148   0.09485  -0.0092   1.0000   0.1416
  -7.250  -0.4522   0.10023   0.09370  -0.0144   1.0000   0.1468
  -7.000  -0.4418   0.09524   0.08861  -0.0132   1.0000   0.1512
  -6.750  -0.4342   0.09258   0.08601  -0.0163   1.0000   0.1590
  -6.250  -0.4148   0.08640   0.07993  -0.0231   1.0000   0.1735
  -6.000  -0.4052   0.08171   0.07531  -0.0205   1.0000   0.1797
  -5.500  -0.3787   0.07561   0.06926  -0.0290   1.0000   0.2011
  -5.250  -0.3642   0.07226   0.06592  -0.0314   1.0000   0.2140
  -5.000  -0.3503   0.06862   0.06230  -0.0324   1.0000   0.2272
  -4.750  -0.3370   0.06483   0.05856  -0.0324   1.0000   0.2411
  -4.500  -0.3236   0.06116   0.05492  -0.0320   1.0000   0.2559
  -4.250  -0.3083   0.05777   0.05156  -0.0322   1.0000   0.2746
  -4.000  -0.2915   0.05437   0.04816  -0.0330   1.0000   0.2979
  -3.750  -0.2753   0.05114   0.04495  -0.0329   1.0000   0.3270
  -3.500  -0.1481   0.03958   0.03152  -0.0643   1.0000   0.1086
  -3.250  -0.1201   0.03597   0.02770  -0.0654   1.0000   0.1036
  -3.000  -0.0866   0.03247   0.02370  -0.0674   1.0000   0.1029
  -2.750  -0.0528   0.02928   0.01993  -0.0689   1.0000   0.1040
  -2.500  -0.0191   0.02630   0.01630  -0.0698   1.0000   0.1052
  -2.250   0.0121   0.02387   0.01342  -0.0699   1.0000   0.1129
  -2.000   0.0407   0.02248   0.01187  -0.0697   1.0000   0.1663
  -1.750   0.0711   0.02035   0.00978  -0.0696   1.0000   0.3053
  -1.500   0.1005   0.01875   0.00824  -0.0695   1.0000   0.3883
  -1.250   0.1296   0.01705   0.00719  -0.0695   1.0000   0.5141
  -1.000   0.1451   0.01561   0.00641  -0.0660   1.0000   1.0000
  -0.750   0.1718   0.01580   0.00598  -0.0658   1.0000   1.0000
  -0.500   0.1971   0.01601   0.00578  -0.0655   1.0000   1.0000
  -0.250   0.2220   0.01624   0.00558  -0.0652   1.0000   1.0000
   0.000   0.2465   0.01649   0.00559  -0.0650   1.0000   1.0000
   0.250   0.2708   0.01677   0.00568  -0.0647   1.0000   1.0000
   0.500   0.2949   0.01707   0.00584  -0.0645   1.0000   1.0000
   0.750   0.3187   0.01740   0.00607  -0.0642   1.0000   1.0000
   1.000   0.3424   0.01775   0.00637  -0.0640   1.0000   1.0000
   1.250   0.3658   0.01814   0.00674  -0.0639   1.0000   1.0000
   1.500   0.3891   0.01856   0.00720  -0.0637   1.0000   1.0000
   1.750   0.4120   0.01901   0.00769  -0.0635   1.0000   1.0000
   2.000   0.4347   0.01951   0.00824  -0.0634   1.0000   1.0000
   2.250   0.4571   0.02005   0.00887  -0.0633   1.0000   1.0000
   2.500   0.4792   0.02064   0.00959  -0.0633   1.0000   1.0000
   2.750   0.5008   0.02130   0.01040  -0.0633   1.0000   1.0000
   3.000   0.5218   0.02204   0.01133  -0.0633   1.0000   1.0000
   3.250   0.5423   0.02288   0.01255  -0.0634   1.0000   1.0000
   3.500   0.5619   0.02384   0.01376  -0.0637   1.0000   1.0000
   3.750   0.5804   0.02498   0.01516  -0.0641   1.0000   1.0000
   4.000   0.6239   0.02636   0.01701  -0.0696   0.9857   1.0000
   4.250   0.8110   0.01926   0.01209  -0.0796   0.7393   1.0000
   4.500   0.8074   0.02315   0.01218  -0.0682   0.2154   1.0000
   4.750   0.8310   0.02592   0.01449  -0.0666   0.1588   1.0000
   5.000   0.8596   0.02842   0.01687  -0.0656   0.1279   1.0000
   5.250   0.8931   0.03152   0.02013  -0.0647   0.1163   1.0000
   5.500   0.9243   0.03541   0.02422  -0.0638   0.1102   1.0000
   5.750   0.9475   0.03856   0.02786  -0.0625   0.0957   1.0000
   6.000   0.9722   0.04275   0.03275  -0.0607   0.0943   1.0000
   6.250   0.9939   0.04765   0.03823  -0.0591   0.0964   1.0000
   6.500   1.0116   0.05264   0.04424  -0.0570   0.1043   1.0000
   6.750   1.0260   0.05859   0.05095  -0.0556   0.1169   1.0000
   7.000   1.0404   0.06577   0.05860  -0.0551   0.1361   1.0000
   7.250   1.0444   0.07677   0.07066  -0.0596   0.2021   1.0000
   7.500   0.9457   0.06885   0.06323  -0.0474   0.1678   1.0000
   7.750   0.9215   0.07632   0.07088  -0.0493   0.1828   1.0000
   8.000   0.8942   0.08385   0.07850  -0.0525   0.2055   1.0000
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