HAM-STD HS1-620 AIRFOIL (hs1620-il)
HAM-STD HS1-620 AIRFOIL - HS1 family of prop airfoils from US Patent No. 4
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(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
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Polars for HAM-STD HS1-620 AIRFOIL (hs1620-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hs1620-il | 50,000 | 9 | 16 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 50,000 | 5 | 25.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 100,000 | 9 | 43.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 100,000 | 5 | 38.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 200,000 | 9 | 59.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 200,000 | 5 | 51.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 500,000 | 9 | 72.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 500,000 | 5 | 57.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1620-il | 1,000,000 | 9 | 76.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1620-il | 1,000,000 | 5 | 70.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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