S2046 (s2046-il)
S2046 - Selig S2046 low Reynolds number airfoil
| Details | Dat file | Parser | |
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(s2046-il) S2046 Selig S2046 low Reynolds number airfoil Max thickness 9% at 26.2% chord. Max camber 2.6% at 55.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S2046 1.00000 0.00000 0.99684 0.00049 0.98756 0.00202 0.97263 0.00462 0.95247 0.00812 0.92737 0.01233 0.89660 0.01717 0.86379 0.02256 0.82624 0.02835 0.78552 0.03433 0.74211 0.04029 0.69650 0.04603 0.64915 0.05136 0.60053 0.05608 0.55108 0.06005 0.50122 0.06316 0.45137 0.06540 0.40203 0.06678 0.35374 0.06732 0.30703 0.06700 0.26243 0.06577 0.22040 0.06357 0.18129 0.06031 0.14539 0.05600 0.11291 0.05071 0.08406 0.04462 0.05912 0.03795 0.03838 0.03089 0.02209 0.02352 0.01036 0.01588 0.00307 0.00813 0.00003 0.00077 0.00000 0.00000 0.00192 -0.00536 0.00922 -0.01059 0.02154 -0.01535 0.03875 -0.01919 0.06092 -0.02200 0.08807 -0.02383 0.12001 -0.02492 0.15629 -0.02542 0.19647 -0.02536 0.24002 -0.02481 0.28644 -0.02373 0.33514 -0.02206 0.38567 -0.01967 0.43769 -0.01655 0.49083 -0.01284 0.54465 -0.00876 0.59863 -0.00461 0.65213 -0.00068 0.70446 0.00276 0.75491 0.00546 0.80269 0.00717 0.84689 0.00768 0.88649 0.00710 0.92073 0.00578 0.94909 0.00412 0.97129 0.00249 0.98721 0.00116 0.99679 0.00030 1.00000 0.00000 |
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Polars for S2046 (s2046-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2046-il | 50,000 | 9 | 38.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 50,000 | 5 | 40.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 100,000 | 9 | 58 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 100,000 | 5 | 55.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 200,000 | 9 | 77.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 200,000 | 5 | 70.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 500,000 | 9 | 101.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 500,000 | 5 | 84.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 1,000,000 | 9 | 108.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 1,000,000 | 5 | 93.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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