NDLI: Experimental investigation of normal shock boundary-layer interaction with hybrid flow control

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Experimental investigation of normal shock boundary-layer interaction with hybrid flow control

Content Provider	NASA Technical Reports Server (NTRS)
Author	Vyas, Manan A. Anderson, Bernhard H. Hirt, Stefanie M.
Copyright Year	2012
Description	Hybrid flow control, a combination of micro-ramps and micro-jets, was experimentally investigated in the 15x15 cm Supersonic Wind Tunnel (SWT) at the NASA Glenn Research Center. Full factorial, a design of experiments (DOE) method, was used to develop a test matrix with variables such as inter-ramp spacing, ramp height and chord length, and micro-jet injection flow ratio. A total of 17 configurations were tested with various parameters to meet the DOE criteria. In addition to boundary-layer measurements, oil flow visualization was used to qualitatively understand shock induced flow separation characteristics. The flow visualization showed the normal shock location, size of the separation, path of the downstream moving counter-rotating vortices, and corner flow effects. The results show that hybrid flow control demonstrates promise in reducing the size of shock boundary-layer interactions and resulting flow separation by means of energizing the boundary layer.
File Size	1594594
Page Count	19
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20120004157
Archival Resource Key	ark:/13960/t80k7c97g
Language	English
Publisher Date	2012-01-07
Access Restriction	Open
Subject Keyword	Aerodynamics Jet Control Jet Flow Vortices Supersonic Wind Tunnels Shock Wave Interaction Size Separation Flow Characteristics Experiment Design Spacing Factorial Design Separated Flow 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

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