SM701 (sm701-il)
SM701 - Somers / Maughmer SM701 airfoil
| Details | Dat file | Parser | |
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(sm701-il) SM701 Somers / Maughmer SM701 airfoil Max thickness 16% at 36.3% chord. Max camber 3% at 60.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SM701 1.00000 0.00000 0.99640 0.00095 0.98605 0.00405 0.96999 0.00946 0.94922 0.01669 0.92431 0.02493 0.89529 0.03348 0.86207 0.04221 0.82498 0.05125 0.78466 0.06055 0.74171 0.06990 0.69676 0.07903 0.65041 0.08760 0.60323 0.09517 0.55548 0.10120 0.50714 0.10557 0.45853 0.10853 0.41019 0.11018 0.36268 0.11055 0.31654 0.10964 0.27229 0.10746 0.23041 0.10397 0.19133 0.09914 0.15541 0.09296 0.12295 0.08544 0.09417 0.07658 0.06915 0.06648 0.04794 0.05534 0.03055 0.04344 0.01701 0.03121 0.00736 0.01910 0.00168 0.00771 0.00016 -0.00212 0.00435 -0.00981 0.01501 -0.01632 0.03127 -0.02244 0.05277 -0.02800 0.07923 -0.03294 0.11036 -0.03726 0.14575 -0.04101 0.18488 -0.04418 0.22722 -0.04670 0.27222 -0.04849 0.31929 -0.04943 0.36784 -0.04938 0.41726 -0.04803 0.46727 -0.04488 0.51811 -0.03983 0.56979 -0.03340 0.62191 -0.02623 0.67386 -0.01887 0.72497 -0.01182 0.77446 -0.00553 0.82144 -0.00041 0.86497 0.00324 0.90406 0.00526 0.93768 0.00567 0.96489 0.00463 0.98462 0.00262 0.99624 0.00073 1.00000 0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for SM701 (sm701-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sm701-il | 50,000 | 9 | 27 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 50,000 | 5 | 30.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 9 | 50.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 100,000 | 5 | 46.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 9 | 68.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 200,000 | 5 | 64.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 9 | 95.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 500,000 | 5 | 79.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 9 | 110.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sm701-il | 1,000,000 | 5 | 93.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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