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HAM-STD HS1-708 AIRFOIL (hs1708-il)

HAM-STD HS1-708 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4


Airfoil hs1708-il
Details Dat file Parser  
(hs1708-il) HAM-STD HS1-708 AIRFOIL
HS1 family of prop airfoils from US Patent No. 4
Max thickness 7.9% at 22% chord.
Max camber 5% at 46% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 HAM-STD HS1-708 AIRFOIL
       62.       62.

   0.00000   0.00013
   0.00050   0.00330
   0.00100   0.00479
   0.00200   0.00704
   0.00300   0.00883
   0.00500   0.01173
   0.00750   0.01461
   0.01000   0.01704
   0.02000   0.02448
   0.03000   0.03017
   0.04000   0.03501
   0.05000   0.03932
   0.06000   0.04326
   0.07000   0.04692
   0.08000   0.05031
   0.09000   0.05344
   0.10000   0.05634
   0.12000   0.06151
   0.14000   0.06595
   0.16000   0.06977
   0.18000   0.07308
   0.20000   0.07587
   0.22000   0.07824
   0.24000   0.08021
   0.26000   0.08182
   0.28000   0.08313
   0.30000   0.08421
   0.34000   0.08583
   0.36000   0.08640
   0.38000   0.08680
   0.40000   0.08701
   0.44000   0.08681
   0.46000   0.08640
   0.48000   0.08579
   0.50000   0.08502
   0.54000   0.08301
   0.56000   0.08176
   0.58000   0.08033
   0.60000   0.07865
   0.64000   0.07443
   0.66000   0.07184
   0.68000   0.06892
   0.70000   0.06570
   0.74000   0.05853
   0.76000   0.05465
   0.78000   0.05062
   0.80000   0.04649
   0.82000   0.04221
   0.84000   0.03798
   0.86000   0.03360
   0.88000   0.02916
   0.90000   0.02462
   0.91000   0.02231
   0.92000   0.01996
   0.93000   0.01757
   0.94000   0.01512
   0.95000   0.01262
   0.96000   0.01005
   0.97000   0.00741
   0.98000   0.00471
   0.99000   0.00196
   1.00000  -0.00086

   0.00000   0.00013
   0.00050  -0.00244
   0.00100  -0.00338
   0.00200  -0.00485
   0.00300  -0.00561
   0.00500  -0.00715
   0.00750  -0.00865
   0.01000  -0.00990
   0.02000  -0.01322
   0.03000  -0.01506
   0.04000  -0.01603
   0.05000  -0.01645
   0.06000  -0.01650
   0.07000  -0.01629
   0.08000  -0.01588
   0.09000  -0.01530
   0.10000  -0.01456
   0.12000  -0.01271
   0.14000  -0.01050
   0.16000  -0.00808
   0.18000  -0.00559
   0.20000  -0.00318
   0.22000  -0.00092
   0.24000   0.00113
   0.26000   0.00293
   0.28000   0.00450
   0.30000   0.00583
   0.34000   0.00791
   0.36000   0.00868
   0.38000   0.00932
   0.40000   0.00984
   0.44000   0.01060
   0.46000   0.01087
   0.48000   0.01106
   0.50000   0.01120
   0.54000   0.01129
   0.56000   0.01125
   0.58000   0.01118
   0.60000   0.01105
   0.64000   0.01065
   0.66000   0.01034
   0.68000   0.00996
   0.70000   0.00947
   0.74000   0.00818
   0.76000   0.00738
   0.78000   0.00650
   0.80000   0.00557
   0.82000   0.00459
   0.84000   0.00356
   0.86000   0.00248
   0.88000   0.00133
   0.90000   0.00006
   0.91000  -0.00058
   0.92000  -0.00128
   0.93000  -0.00196
   0.94000  -0.00268
   0.95000  -0.00341
   0.96000  -0.00416
   0.97000  -0.00493
   0.98000  -0.00572
   0.99000  -0.00652
   1.00000  -0.00734

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Polars for HAM-STD HS1-708 AIRFOIL (hs1708-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hs1708-il50,000942.8 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1708-il50,000543 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1708-il100,000967.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1708-il100,000566.5 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1708-il200,000997.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1708-il200,000592.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1708-il500,0009139.5 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1708-il500,0005120.8 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1708-il1,000,0009169 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1708-il1,000,0005117 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
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