HAM-STD HS1-708 AIRFOIL (hs1708-il)
HAM-STD HS1-708 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hs1708-il | 50,000 | 9 | 42.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 50,000 | 5 | 43 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 100,000 | 9 | 67.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 100,000 | 5 | 66.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 200,000 | 9 | 97.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 200,000 | 5 | 92.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 500,000 | 9 | 139.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 500,000 | 5 | 120.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1708-il | 1,000,000 | 9 | 169 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1708-il | 1,000,000 | 5 | 117 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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