S6061 9% (s6061-il)
S6061 9% - Selig S6061 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s6061-il) S6061 9% Selig S6061 low Reynolds number airfoil Max thickness 9% at 34% chord. Max camber 1.5% at 43.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S6061 9%
1.00000 0.00000
0.99674 0.00022
0.98707 0.00100
0.97131 0.00255
0.94987 0.00497
0.92321 0.00829
0.89186 0.01244
0.85637 0.01728
0.81726 0.02264
0.77507 0.02832
0.73032 0.03410
0.68352 0.03977
0.63517 0.04512
0.58576 0.05001
0.53580 0.05427
0.48580 0.05776
0.43623 0.06032
0.38750 0.06185
0.34000 0.06231
0.29417 0.06175
0.25047 0.06018
0.20931 0.05761
0.17107 0.05408
0.13608 0.04961
0.10463 0.04431
0.07697 0.03826
0.05331 0.03161
0.03379 0.02455
0.01856 0.01732
0.00771 0.01020
0.00135 0.00364
0.00030 -0.00161
0.00507 -0.00618
0.01525 -0.01080
0.03050 -0.01506
0.05071 -0.01880
0.07572 -0.02193
0.10534 -0.02443
0.13931 -0.02629
0.17729 -0.02754
0.21892 -0.02821
0.26374 -0.02836
0.31128 -0.02804
0.36098 -0.02729
0.41230 -0.02615
0.46466 -0.02466
0.51746 -0.02284
0.57012 -0.02070
0.62210 -0.01826
0.67288 -0.01560
0.72194 -0.01280
0.76876 -0.01002
0.81279 -0.00739
0.85345 -0.00507
0.89016 -0.00317
0.92237 -0.00173
0.94954 -0.00076
0.97124 -0.00020
0.98708 0.00002
0.99674 0.00003
1.00000 0.00000
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Similar airfoils
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Polars for S6061 9% (s6061-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s6061-il | 50,000 | 9 | 34.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6061-il | 50,000 | 5 | 35.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6061-il | 100,000 | 9 | 51.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6061-il | 100,000 | 5 | 50.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6061-il | 200,000 | 9 | 68.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6061-il | 200,000 | 5 | 63.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6061-il | 500,000 | 9 | 88.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6061-il | 500,000 | 5 | 77.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s6061-il | 1,000,000 | 9 | 102 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s6061-il | 1,000,000 | 5 | 81.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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