MH 61 10.26% (mh61-il)
MH 61 10.26% - Martin Hepperle MH 61 for flying wings
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(mh61-il) MH 61 10.26% Martin Hepperle MH 61 for flying wings Max thickness 10.2% at 27.6% chord. Max camber 1.4% at 37.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
MH 61 10.26% 1.00000000 0.00000000 0.99662552 -0.00021296 0.98634442 -0.00058867 0.96924455 -0.00047375 0.94585731 0.00056315 0.91673505 0.00269474 0.88251392 0.00609338 0.84398992 0.01077369 0.80195531 0.01656917 0.75715989 0.02322682 0.71033087 0.03042633 0.66215348 0.03775213 0.61314451 0.04471331 0.56364860 0.05095356 0.51402085 0.05625665 0.46462009 0.06047633 0.41583230 0.06354070 0.36806914 0.06540775 0.32175184 0.06606308 0.27730980 0.06549720 0.23513530 0.06369756 0.19557573 0.06068599 0.15893920 0.05651303 0.12547935 0.05129165 0.09546190 0.04520923 0.06917074 0.03845040 0.04684813 0.03119300 0.02868571 0.02363888 0.01483234 0.01603750 0.00540062 0.00871984 0.00224694 0.00512990 0.00104319 0.00323637 0.00027501 0.00148232 0.00002448 0.00041540 0.00004474 -0.00052570 0.00040935 -0.00141651 0.00109497 -0.00235178 0.00259141 -0.00381107 0.00459453 -0.00532859 0.00868086 -0.00781260 0.02108735 -0.01314311 0.03837857 -0.01833977 0.06030248 -0.02318942 0.08663912 -0.02748653 0.11716742 -0.03106570 0.15167904 -0.03381596 0.18990853 -0.03569772 0.23155319 -0.03669930 0.27626006 -0.03685835 0.32363710 -0.03624306 0.37322832 -0.03497025 0.42452356 -0.03316183 0.47695565 -0.03096354 0.52990961 -0.02849367 0.58275075 -0.02586412 0.63483287 -0.02315568 0.68551931 -0.02044124 0.73418958 -0.01776873 0.78025217 -0.01518546 0.82314952 -0.01272468 0.86235287 -0.01042910 0.89736920 -0.00831193 0.92776030 -0.00638577 0.95314575 -0.00464029 0.97320761 -0.00306517 0.98776461 -0.00159794 0.99682854 -0.00043667 1.00000000 0.00000000 |
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Polars for MH 61 10.26% (mh61-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh61-il | 50,000 | 9 | 31.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 50,000 | 5 | 33 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 100,000 | 9 | 47.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 100,000 | 5 | 47.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 200,000 | 9 | 63.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 200,000 | 5 | 60.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 500,000 | 9 | 84.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 500,000 | 5 | 76.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh61-il | 1,000,000 | 9 | 98 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh61-il | 1,000,000 | 5 | 86.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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