Hypersonic laminar flow control
US10071798B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 19, 2013 |
| Grant date | Sep 11, 2018 |
| Priority date | — |
| Expiry date | May 16, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/10
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A novel passive control technique for laminar flow over air transportation vehicles and space reentry vehicles flying at high supersonic and hypersonic speeds is disclosed. The control of laminar flow can be achieved by applying an array of surface roughness elements in the region before the laminar-turbulent transition. For example, an array of two-dimensional rings, stripes, or closely packed three-dimensional isolated roughness elements may be used to stabilize the instability waves and delay transition. The roughness elements may have a height between 40% and 60% of the local boundary-layer thickness. The exact location, height, and spacing of surface roughness elements may be determined by a numerical simulation strategy based on the most unstable second mode, e.g. using known eN transition prediction method, experimental measurement, or any other suitable technique.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.