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Experimental investigation of the flow on the suction side of a thin delta wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hummel, D. |
| Copyright Year | 1981 |
| Description | Surface oil flow patterns were photographed and pressure distribution measurements were carried out on a sharp edged delta wing of aspect ratio lambda = 1.0 in order to determine the influence of Reynolds number and of vortex breakdown on the flow on the suction side of the wing. The formation of the secondary vortex occurs due to separation of a laminar boundary layer in the front part of the wing and due to separation of a turbulent boundary layer in the rear part of the wing. In the case of turbulent separation, the secondary separation line is closer to the wing leading edge than in the laminar case. The position of the transition depends on the Reynolds number and on the angle of incidence. The breakdown of a vortex above the wing leads to a kink in the secondary separation line. |
| File Size | 726206 |
| Page Count | 15 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19810012495 |
| Archival Resource Key | ark:/13960/t5hb3z386 |
| Language | English |
| Publisher Date | 1981-03-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Boundary Layer Separation Suction Laminar Boundary Layer Reynolds Number Delta Wings Flow Distribution Turbulent Boundary Layer Thin Wings Boundary Layer Transition Vortex Breakdown Leading Edges Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
