S1016 (s1016-il)
S1016 - Selig S1016 HPV airfoil
| Details | Dat file | Parser | |
|
(s1016-il) S1016 Selig S1016 HPV airfoil Max thickness 17.5% at 41.8% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S1016
1.00000 0.00000
0.99598 0.00024
0.98419 0.00132
0.96527 0.00383
0.93999 0.00803
0.90913 0.01406
0.87362 0.02204
0.83461 0.03184
0.79341 0.04301
0.75133 0.05437
0.70854 0.06404
0.66386 0.07130
0.61693 0.07689
0.56837 0.08122
0.51871 0.08437
0.46855 0.08643
0.41848 0.08742
0.36907 0.08736
0.32090 0.08627
0.27453 0.08416
0.23048 0.08103
0.18925 0.07691
0.15132 0.07179
0.11710 0.06566
0.08694 0.05853
0.06108 0.05037
0.03965 0.04127
0.02273 0.03137
0.01038 0.02091
0.00267 0.01025
0.00000 0.00000
0.00267 -0.01025
0.01038 -0.02091
0.02273 -0.03137
0.03965 -0.04127
0.06108 -0.05037
0.08694 -0.05853
0.11710 -0.06566
0.15132 -0.07179
0.18925 -0.07691
0.23048 -0.08103
0.27453 -0.08416
0.32090 -0.08627
0.36907 -0.08736
0.41848 -0.08742
0.46855 -0.08643
0.51871 -0.08437
0.56837 -0.08122
0.61693 -0.07689
0.66386 -0.07130
0.70854 -0.06404
0.75133 -0.05437
0.79341 -0.04301
0.83461 -0.03184
0.87362 -0.02204
0.90913 -0.01406
0.93999 -0.00803
0.96527 -0.00383
0.98419 -0.00132
0.99598 -0.00024
1.00000 0.00000
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Polars for S1016 (s1016-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1016-il | 50,000 | 9 | 28.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 50,000 | 5 | 22.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 9 | 39.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 5 | 23.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 9 | 35.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 5 | 30.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 9 | 40.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 5 | 41.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 9 | 52.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 5 | 52 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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