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 HS1-606 AIRFOIL (hs1606-il)

HAM-STD HS1-606 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4


Airfoil hs1606-il
Details Dat file Parser  
(hs1606-il) HAM-STD HS1-606 AIRFOIL
HS1 family of prop airfoils from US Patent No. 4
Max thickness 6% at 18% chord.
Max camber 4.4% at 46% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 HAM-STD HS1-606 AIRFOIL
       62.       62.

   0.00000   0.00015
   0.00050   0.00259
   0.00100   0.00379
   0.00200   0.00562
   0.00300   0.00708
   0.00500   0.00938
   0.00750   0.01164
   0.01000   0.01352
   0.02000   0.01926
   0.03000   0.02371
   0.04000   0.02756
   0.05000   0.03105
   0.06000   0.03429
   0.07000   0.03731
   0.08000   0.04012
   0.09000   0.04273
   0.10000   0.04515
   0.12000   0.04946
   0.14000   0.05318
   0.16000   0.05638
   0.18000   0.05915
   0.20000   0.06153
   0.22000   0.06354
   0.24000   0.06522
   0.26000   0.06659
   0.28000   0.06772
   0.30000   0.06865
   0.34000   0.07005
   0.36000   0.07056
   0.38000   0.07092
   0.40000   0.07112
   0.44000   0.07100
   0.46000   0.07069
   0.48000   0.07021
   0.50000   0.06959
   0.54000   0.06796
   0.56000   0.06695
   0.58000   0.06578
   0.60000   0.06442
   0.64000   0.06098
   0.66000   0.05886
   0.68000   0.05647
   0.70000   0.05383
   0.74000   0.04794
   0.76000   0.04474
   0.78000   0.04142
   0.80000   0.03802
   0.82000   0.03453
   0.84000   0.03099
   0.86000   0.02738
   0.88000   0.02371
   0.90000   0.01996
   0.91000   0.01804
   0.92000   0.01616
   0.93000   0.01411
   0.94000   0.01209
   0.95000   0.01001
   0.96000   0.00788
   0.97000   0.00570
   0.98000   0.00346
   0.99000   0.00118
   1.00000  -0.00115

   0.00000   0.00015
   0.00050  -0.00162
   0.00100  -0.00220
   0.00200  -0.00296
   0.00300  -0.00354
   0.00500  -0.00455
   0.00750  -0.00563
   0.01000  -0.00656
   0.02000  -0.00925
   0.03000  -0.01079
   0.04000  -0.01160
   0.05000  -0.01190
   0.06000  -0.01187
   0.07000  -0.01161
   0.08000  -0.01118
   0.09000  -0.01060
   0.10000  -0.00988
   0.12000  -0.00807
   0.14000  -0.00588
   0.16000  -0.00347
   0.18000  -0.00099
   0.20000   0.00143
   0.22000   0.00367
   0.24000   0.00565
   0.26000   0.00734
   0.28000   0.00875
   0.30000   0.00992
   0.34000   0.01167
   0.36000   0.01231
   0.38000   0.01284
   0.40000   0.01326
   0.44000   0.01387
   0.46000   0.01406
   0.48000   0.01419
   0.50000   0.01425
   0.54000   0.01420
   0.56000   0.01409
   0.58000   0.01394
   0.60000   0.01373
   0.64000   0.01314
   0.66000   0.01273
   0.68000   0.01224
   0.70000   0.01165
   0.74000   0.01018
   0.76000   0.00930
   0.78000   0.00835
   0.80000   0.00734
   0.82000   0.00630
   0.84000   0.00522
   0.86000   0.00408
   0.88000   0.00288
   0.90000   0.00161
   0.91000   0.00094
   0.92000   0.00025
   0.93000  -0.00046
   0.94000  -0.00119
   0.95000  -0.00193
   0.96000  -0.00289
   0.97000  -0.00346
   0.98000  -0.00425
   0.99000  -0.00508
   1.00000  -0.00589

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

ARA-D 6% AIRFOILPreviewDetails
GOE 400 AIRFOILPreviewDetails
GM15 (smoothed)PreviewDetails
GOE 121 (MVA H.1) AIRFOILPreviewDetails
GOE 57 AIRFOILPreviewDetails
GOE 335 (D.F.W.) AIRFOILPreviewDetails
GOE 100 (SOPWITH) AIRFOILPreviewDetails
GOE 235 (SCHTTE-LANZ) AIRFOILPreviewDetails
GOE 362 AIRFOILPreviewDetails
GOE 494 AIRFOILPreviewDetails

Polars for HAM-STD HS1-606 AIRFOIL (hs1606-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   hs1606-il50,000945.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1606-il50,000545 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1606-il100,000968.5 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1606-il100,000566.3 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1606-il200,000995.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1606-il200,000590.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1606-il500,0009133.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1606-il500,0005121.9 at α=2.25°Mach=0 Ncrit=5Xfoil predictionDetails
   hs1606-il1,000,0009160.5 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   hs1606-il1,000,0005108.4 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit