Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HAM-STD HS1-620 AIRFOIL (hs1620-il)

HAM-STD HS1-620 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4


Airfoil hs1620-il
Details Dat file Parser  
(hs1620-il) HAM-STD HS1-620 AIRFOIL
HS1 family of prop airfoils from US Patent No. 4
Max thickness 20% at 34% chord.
Max camber 4.1% at 44% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 HAM-STD HS1-620 AIRFOIL
       62.       62.

   0.00000   0.00001
   0.00050   0.00694
   0.00100   0.00993
   0.00200   0.01424
   0.00300   0.01760
   0.00500   0.02300
   0.00750   0.02845
   0.01000   0.03306
   0.02000   0.04737
   0.03000   0.05820
   0.04000   0.06713
   0.05000   0.07477
   0.06000   0.08147
   0.07000   0.08742
   0.08000   0.09274
   0.09000   0.09755
   0.10000   0.10190
   0.12000   0.10943
   0.14000   0.11566
   0.16000   0.12079
   0.18000   0.12501
   0.20000   0.12844
   0.22000   0.13121
   0.24000   0.13344
   0.26000   0.13524
   0.28000   0.13670
   0.30000   0.13789
   0.34000   0.13955
   0.36000   0.14000
   0.38000   0.14017
   0.40000   0.14007
   0.44000   0.13904
   0.46000   0.13814
   0.48000   0.13699
   0.50000   0.13556
   0.54000   0.13189
   0.56000   0.12963
   0.58000   0.12711
   0.60000   0.12435
   0.64000   0.11823
   0.66000   0.11489
   0.68000   0.11138
   0.70000   0.10770
   0.74000   0.09981
   0.76000   0.09560
   0.78000   0.09118
   0.80000   0.08651
   0.82000   0.08153
   0.84000   0.07616
   0.86000   0.07031
   0.88000   0.06391
   0.90000   0.05693
   0.91000   0.05322
   0.92000   0.04939
   0.93000   0.04545
   0.94000   0.04142
   0.95000   0.03727
   0.96000   0.03295
   0.97000   0.02840
   0.98000   0.02353
   0.99000   0.01831
   1.00000   0.01272

   0.00000   0.00001
   0.00050  -0.00650
   0.00100  -0.00907
   0.00200  -0.01258
   0.00300  -0.01520
   0.00500  -0.01922
   0.00750  -0.02308
   0.01000  -0.02621
   0.02000  -0.03521
   0.03000  -0.04139
   0.04000  -0.04609
   0.05000  -0.04983
   0.06000  -0.05289
   0.07000  -0.05541
   0.08000  -0.05751
   0.09000  -0.05925
   0.10000  -0.06070
   0.12000  -0.06280
   0.14000  -0.06404
   0.16000  -0.06459
   0.18000  -0.06463
   0.20000  -0.06430
   0.22000  -0.06376
   0.24000  -0.06317
   0.26000  -0.06261
   0.28000  -0.06211
   0.30000  -0.06163
   0.34000  -0.06061
   0.36000  -0.06000
   0.38000  -0.05932
   0.40000  -0.05859
   0.44000  -0.05705
   0.46000  -0.05626
   0.48000  -0.05545
   0.50000  -0.05459
   0.54000  -0.05269
   0.56000  -0.05161
   0.58000  -0.05045
   0.60000  -0.04919
   0.64000  -0.04645
   0.66000  -0.04499
   0.68000  -0.04348
   0.70000  -0.04197
   0.74000  -0.03900
   0.76000  -0.03755
   0.78000  -0.03610
   0.80000  -0.03462
   0.82000  -0.03307
   0.84000  -0.03144
   0.86000  -0.02972
   0.88000  -0.02790
   0.90000  -0.02600
   0.91000  -0.02502
   0.92000  -0.02401
   0.93000  -0.02297
   0.94000  -0.02189
   0.95000  -0.02078
   0.96000  -0.01963
   0.97000  -0.01843
   0.98000  -0.01716
   0.99000  -0.01580
   1.00000  -0.01427

Dat file parser warnings
  • Line 127 - Invalid characters : 
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 66-S-196 V1 AIRFOILPreviewDetails
FX 66-S-196 AIRFOILPreviewDetails
FX S 02-196 AIRFOILPreviewDetails
EPPLER 857 AIRFOILPreviewDetails
NACA 5-H-20 AIRFOILPreviewDetails
GOE 424 AIRFOILPreviewDetails
NACA 4421PreviewDetails
GOE 383 AIRFOILPreviewDetails
WORTMANN FX 66-17AII-182 AIRFOIL (ASPreviewDetails
GOE 420 AIRFOILPreviewDetails

Polars for HAM-STD HS1-620 AIRFOIL (hs1620-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hs1620-il50,000916 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1620-il50,000525.2 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1620-il100,000943.6 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1620-il100,000538.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1620-il200,000959.4 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1620-il200,000551.2 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1620-il500,000972.2 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1620-il500,000557.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1620-il1,000,000976.3 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1620-il1,000,000570.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit