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Effects of hybrid flow control on a normal shock boundary-layer interaction
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Vyas, Manan A. Hirt, Stefanie M. |
| Copyright Year | 2013 |
| Description | Hybrid flow control, a combination of micro-ramps and steady micro-jets, was experimentally investigated in the 15x15 cm Supersonic Wind Tunnel at the NASA Glenn Research Center. A central composite design of experiments method, was used to develop response surfaces for boundary-layer thickness and reversed-flow thickness, with factor variables of inter-ramp spacing, ramp height and chord length, and flow injection ratio. Boundary-layer measurements and wall static pressure data were used to understand flow separation characteristics. A limited number of profiles were measured in the corners of the tunnel to aid in understanding the three-dimensional characteristics of the flowfield. |
| File Size | 1636485 |
| Page Count | 23 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20150007505 |
| Archival Resource Key | ark:/13960/t8sb93261 |
| Language | English |
| Publisher Date | 2013-01-07 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Wall Pressure Reversed Flow Jet Flow Vortices Supersonic Wind Tunnels Flow Distribution Shock Wave Interaction Experiment Design Spacing Factorial Design Boundary Layer Flow Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
