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HAM-STD HS1-430 AIRFOIL (hs1430-il)

HAM-STD HS1-430 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4


Airfoil hs1430-il
Details Dat file Parser  
(hs1430-il) HAM-STD HS1-430 AIRFOIL
HS1 family of prop airfoils from US Patent No. 4
Max thickness 30% at 34% chord.
Max camber 3% at 44% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 HAM-STD HS1-430 AIRFOIL
       62.       62.

   0.00000   0.00000
   0.00050   0.01024
   0.00100   0.01456
   0.00200   0.02071
   0.00300   0.02547
   0.00500   0.03303
   0.00750   0.04057
   0.01000   0.04692
   0.02000   0.06627
   0.03000   0.08068
   0.04000   0.09241
   0.05000   0.10235
   0.06000   0.11097
   0.07000   0.11857
   0.08000   0.12534
   0.09000   0.13138
   0.10000   0.13680
   0.12000   0.14595
   0.14000   0.15325
   0.16000   0.15904
   0.18000   0.16517
   0.20000   0.16723
   0.22000   0.17011
   0.24000   0.17243
   0.26000   0.17433
   0.28000   0.17587
   0.30000   0.17708
   0.34000   0.17851
   0.36000   0.17872
   0.38000   0.17857
   0.40000   0.17808
   0.44000   0.17626
   0.46000   0.17497
   0.48000   0.17342
   0.50000   0.17156
   0.54000   0.16680
   0.56000   0.16388
   0.58000   0.16062
   0.60000   0.15707
   0.64000   0.14920
   0.66000   0.14493
   0.68000   0.14045
   0.70000   0.13577
   0.74000   0.12588
   0.76000   0.12064
   0.78000   0.11518
   0.80000   0.10942
   0.82000   0.10329
   0.84000   0.09670
   0.86000   0.08955
   0.88000   0.08178
   0.90000   0.07334
   0.91000   0.06850
   0.92000   0.06420
   0.93000   0.05938
   0.94000   0.05440
   0.95000   0.04927
   0.96000   0.04396
   0.97000   0.03846
   0.98000   0.03267
   0.99000   0.02649
   1.00000   0.01969

   0.00000   0.00001
   0.00050  -0.00991
   0.00100  -0.01393
   0.00200  -0.01951
   0.00300  -0.02372
   0.00500  -0.03028
   0.00750  -0.03668
   0.01000  -0.04196
   0.02000  -0.05751
   0.03000  -0.06858
   0.04000  -0.07728
   0.05000  -0.08441
   0.06000  -0.09041
   0.07000  -0.09554
   0.08000  -0.09995
   0.09000  -0.10376
   0.10000  -0.10707
   0.12000  -0.11231
   0.14000  -0.11605
   0.16000  -0.11859
   0.18000  -0.12064
   0.20000  -0.12114
   0.22000  -0.12164
   0.24000  -0.12190
   0.26000  -0.12202
   0.28000  -0.12204
   0.30000  -0.12197
   0.34000  -0.12145
   0.36000  -0.12096
   0.38000  -0.12030
   0.40000  -0.11948
   0.44000  -0.11742
   0.46000  -0.11622
   0.48000  -0.11489
   0.50000  -0.11340
   0.54000  -0.10987
   0.56000  -0.10780
   0.58000  -0.10553
   0.60000  -0.10307
   0.64000  -0.09765
   0.66000  -0.09472
   0.68000  -0.09168
   0.70000  -0.08857
   0.74000  -0.08220
   0.76000  -0.07895
   0.78000  -0.07562
   0.80000  -0.07216
   0.82000  -0.06850
   0.84000  -0.06459
   0.86000  -0.06040
   0.88000  -0.05590
   0.90000  -0.05109
   0.91000  -0.04855
   0.92000  -0.04594
   0.93000  -0.04323
   0.94000  -0.04043
   0.95000  -0.03754
   0.96000  -0.03455
   0.97000  -0.03145
   0.98000  -0.02818
   0.99000  -0.02467
   1.00000  -0.02080

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Polars for HAM-STD HS1-430 AIRFOIL (hs1430-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hs1430-il50,000916.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1430-il50,000514.2 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1430-il100,000928.7 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1430-il100,000521.2 at α=10°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1430-il200,000931 at α=10.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1430-il200,000522.4 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1430-il500,000927.4 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1430-il500,000523.6 at α=10.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1430-il1,000,000929.2 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1430-il1,000,000529.1 at α=12.5°Mach=0 Ncrit=5Xfoil predictionDetails
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