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HAM-STD HS1-404 AIRFOIL (hs1404-il)

HAM-STD HS1-404 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4


Airfoil hs1404-il
Details Dat file Parser  
(hs1404-il) HAM-STD HS1-404 AIRFOIL
HS1 family of prop airfoils from US Patent No. 4
Max thickness 4% at 18% chord.
Max camber 3.1% at 46% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 HAM-STD HS1-404 AIRFOIL
       62.       62.

   0.00000   0.00009
   0.00050   0.00171
   0.00100   0.00250
   0.00200   0.00372
   0.00300   0.00470
   0.00500   0.00628
   0.00750   0.00788
   0.01000   0.00923
   0.02000   0.01339
   0.03000   0.01655
   0.04000   0.01922
   0.05000   0.02158
   0.06000   0.02375
   0.07000   0.02577
   0.08000   0.02766
   0.09000   0.02943
   0.10000   0.03107
   0.12000   0.03403
   0.14000   0.03659
   0.16000   0.03883
   0.18000   0.04077
   0.20000   0.04244
   0.22000   0.04386
   0.24000   0.04504
   0.26000   0.04601
   0.28000   0.04680
   0.30000   0.04745
   0.34000   0.04844
   0.36000   0.04880
   0.38000   0.04906
   0.40000   0.04920
   0.44000   0.04914
   0.46000   0.04893
   0.48000   0.04860
   0.50000   0.04818
   0.54000   0.04705
   0.56000   0.04635
   0.58000   0.04555
   0.60000   0.04461
   0.64000   0.04223
   0.66000   0.04076
   0.68000   0.03911
   0.70000   0.03728
   0.74000   0.03319
   0.76000   0.03097
   0.78000   0.02867
   0.80000   0.02631
   0.82000   0.02389
   0.84000   0.02143
   0.86000   0.01892
   0.88000   0.01637
   0.90000   0.01376
   0.91000   0.01243
   0.92000   0.01108
   0.93000   0.00970
   0.94000   0.00829
   0.95000   0.00684
   0.96000   0.00536
   0.97000   0.00384
   0.98000   0.00229
   0.99000   0.00070
   1.00000  -0.00092

   0.00000   0.00004
   0.00050  -0.00113
   0.00100  -0.00155
   0.00200  -0.00210
   0.00300  -0.00253
   0.00500  -0.00323
   0.00750  -0.00395
   0.01000  -0.00455
   0.02000  -0.00620
   0.03000  -0.00709
   0.04000  -0.00751
   0.05000  -0.00761
   0.06000  -0.00756
   0.07000  -0.00724
   0.08000  -0.00686
   0.09000  -0.00639
   0.10000  -0.00584
   0.12000  -0.00451
   0.14000  -0.00295
   0.16000  -0.00123
   0.18000   0.00055
   0.20000   0.00230
   0.22000   0.00393
   0.24000   0.00536
   0.26000   0.00658
   0.28000   0.00758
   0.30000   0.00840
   0.34000   0.00961
   0.36000   0.01007
   0.38000   0.01044
   0.40000   0.01074
   0.44000   0.01116
   0.46000   0.01129
   0.48000   0.01137
   0.50000   0.01139
   0.54000   0.01132
   0.56000   0.01122
   0.58000   0.01108
   0.60000   0.01091
   0.64000   0.01043
   0.66000   0.01010
   0.68000   0.00991
   0.70000   0.00924
   0.74000   0.00809
   0.76000   0.00741
   0.78000   0.00668
   0.80000   0.00591
   0.82000   0.00512
   0.84000   0.00429
   0.86000   0.00343
   0.88000   0.00252
   0.90000   0.00156
   0.91000   0.00106
   0.92000   0.00054
   0.93000   0.00000
   0.94000  -0.00054
   0.95000  -0.00110
   0.96000  -0.00167
   0.97000  -0.00225
   0.98000  -0.00285
   0.99000  -0.00346
   1.00000  -0.00408

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Polars for HAM-STD HS1-404 AIRFOIL (hs1404-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hs1404-il50,000942.1 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1404-il50,000542.5 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1404-il100,000559.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1404-il200,000984.5 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1404-il200,000578.6 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1404-il500,0009114.7 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1404-il500,0005102.2 at α=1.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1404-il1,000,0009134.6 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1404-il1,000,0005113.3 at α=1.25°Mach=0 Ncrit=5Xfoil predictionDetails
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