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HAM-STD HS1-712 AIRFOIL (hs1712-il)

HAM-STD HS1-712 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4


Airfoil hs1712-il
Details Dat file Parser  
(hs1712-il) HAM-STD HS1-712 AIRFOIL
HS1 family of prop airfoils from US Patent No. 4
Max thickness 12% at 36% chord.
Max camber 4.9% at 44% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 HAM-STD HS1-712 AIRFOIL
       62.       62.

   0.00000   0.00001
   0.00050   0.00430
   0.00100   0.00600
   0.00200   0.00903
   0.00300   0.01127
   0.00500   0.01490
   0.00750   0.01861
   0.01000   0.02180
   0.02000   0.03186
   0.03000   0.03967
   0.04000   0.04688
   0.05000   0.05192
   0.06000   0.05698
   0.07000   0.06110
   0.08000   0.06562
   0.09000   0.06937
   0.10000   0.07280
   0.12000   0.07886
   0.14000   0.08401
   0.16000   0.08839
   0.18000   0.09211
   0.20000   0.09525
   0.22000   0.09786
   0.24000   0.10000
   0.26000   0.10173
   0.28000   0.10313
   0.30000   0.10418
   0.34000   0.10542
   0.36000   0.10632
   0.38000   0.10687
   0.40000   0.10700
   0.44000   0.10656
   0.46000   0.10600
   0.48000   0.10526
   0.50000   0.10423
   0.54000   0.10154
   0.56000   0.09965
   0.58000   0.09795
   0.60000   0.09587
   0.64000   0.09125
   0.66000   0.08872
   0.68000   0.08605
   0.70000   0.08322
   0.74000   0.07789
   0.76000   0.07477
   0.78000   0.07028
   0.80000   0.06668
   0.82000   0.06262
   0.84000   0.05834
   0.86000   0.05368
   0.88000   0.04856
   0.90000   0.04299
   0.91000   0.03997
   0.92000   0.03686
   0.93000   0.03364
   0.94000   0.03032
   0.95000   0.02689
   0.96000   0.02335
   0.97000   0.01968
   0.98000   0.01570
   0.99000   0.01171
   1.00000   0.00720

   0.00000   0.00000
   0.00050  -0.00377
   0.00100  -0.00519
   0.00200  -0.00709
   0.00300  -0.00842
   0.00500  -0.01044
   0.00750  -0.01230
   0.01000  -0.01376
   0.02000  -0.01767
   0.03000  -0.02006
   0.04000  -0.02109
   0.05000  -0.02283
   0.06000  -0.02353
   0.07000  -0.02417
   0.08000  -0.02450
   0.09000  -0.02466
   0.10000  -0.02469
   0.12000  -0.02440
   0.14000  -0.02374
   0.16000  -0.02279
   0.18000  -0.02159
   0.20000  -0.02030
   0.22000  -0.01901
   0.24000  -0.01786
   0.26000  -0.01688
   0.28000  -0.01607
   0.30000  -0.01536
   0.34000  -0.01389
   0.36000  -0.01344
   0.38000  -0.01279
   0.40000  -0.01216
   0.44000  -0.01105
   0.46000  -0.01060
   0.48000  -0.01020
   0.50000  -0.00985
   0.54000  -0.00919
   0.56000  -0.00888
   0.58000  -0.00856
   0.60000  -0.00824
   0.64000  -0.00756
   0.66000  -0.00721
   0.68000  -0.00687
   0.70000  -0.00658
   0.74000  -0.00619
   0.76000  -0.00611
   0.78000  -0.00609
   0.80000  -0.00611
   0.82000  -0.00614
   0.84000  -0.00621
   0.86000  -0.00633
   0.88000  -0.00653
   0.90000  -0.00683
   0.91000  -0.00701
   0.92000  -0.00721
   0.93000  -0.00742
   0.94000  -0.00753
   0.95000  -0.00785
   0.96000  -0.00807
   0.97000  -0.00829
   0.98000  -0.00882
   0.99000  -0.00976
   1.00000  -0.01070

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Polars for HAM-STD HS1-712 AIRFOIL (hs1712-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hs1712-il50,000936.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1712-il50,000538.3 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1712-il100,000960.7 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1712-il100,000558.4 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1712-il200,000982.8 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1712-il200,000574.7 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1712-il500,0009103.4 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1712-il500,000583.5 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1712-il1,000,0009103.7 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1712-il1,000,000589.7 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
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