MH 120 11.57% (mh120-il)
MH 120 11.57% - Martin Hepperle MH 120 for tip section of a propeller
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(mh120-il) MH 120 11.57% Martin Hepperle MH 120 for tip section of a propeller Max thickness 11.6% at 34.7% chord. Max camber 2.2% at 44.2% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 120 11.57% 1.00000000 0.00000000 0.99657719 0.00137690 0.98685087 0.00402821 0.97139506 0.00734876 0.95028213 0.01142090 0.92396594 0.01633315 0.89296043 0.02204560 0.85780483 0.02840960 0.81908793 0.03525874 0.77729819 0.04226202 0.73286713 0.04927267 0.68630523 0.05615183 0.63825561 0.06277069 0.58927764 0.06882005 0.53990087 0.07410860 0.49058966 0.07836275 0.44179403 0.08144146 0.39389925 0.08314630 0.34727098 0.08342625 0.30221961 0.08220339 0.25902829 0.07958612 0.21804994 0.07573212 0.17975005 0.07080805 0.14451023 0.06483273 0.11261875 0.05792996 0.08433629 0.05022699 0.05990560 0.04191067 0.03950438 0.03313028 0.02321643 0.02413907 0.01111339 0.01529771 0.00331128 0.00708273 0.00000653 0.00027180 0.00274905 -0.00489326 0.01208439 -0.00949772 0.02693935 -0.01408758 0.04695631 -0.01840810 0.07183908 -0.02234304 0.10132479 -0.02576277 0.13506812 -0.02863344 0.17271490 -0.03081287 0.21392048 -0.03227113 0.25831820 -0.03293283 0.30552817 -0.03286935 0.35509959 -0.03211215 0.40653191 -0.03080365 0.45928215 -0.02899266 0.51278852 -0.02685901 0.56642343 -0.02449212 0.61952117 -0.02205631 0.67141946 -0.01957024 0.72148058 -0.01715410 0.76907228 -0.01481514 0.81358745 -0.01264343 0.85444687 -0.01061865 0.89111556 -0.00878945 0.92309812 -0.00711619 0.94995641 -0.00559511 0.97129402 -0.00417387 0.98679018 -0.00268254 0.99652851 -0.00105272 1.00000000 0.00000000 |
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Polars for MH 120 11.57% (mh120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh120-il | 50,000 | 9 | 32.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 50,000 | 5 | 34.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 100,000 | 9 | 54.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 100,000 | 5 | 54.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 200,000 | 9 | 76.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 200,000 | 5 | 73.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 500,000 | 9 | 104.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 500,000 | 5 | 95.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh120-il | 1,000,000 | 9 | 124.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh120-il | 1,000,000 | 5 | 105.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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