- Author: Vivek V Kumar
- Date: 26 Jun 2012
- Publisher: LAP Lambert Academic Publishing
- Original Languages: English
- Format: Paperback::100 pages
- ISBN10: 3659158348
- ISBN13: 9783659158346
- Publication City/Country: Saarbrucken, Germany
- Dimension: 152x 229x 6mm::159g
- Download Link: Effect of Micro-Vortex Generator in Hypersonic Inlet
Micro-ramps for hypersonic flow control. MR Saad, H Micro-Ramps in Mach 5 hypersonic flow Study on the Effect of Bluff Body with Slit in the Micro-Channel Combustor. W Shuib, AC Microvortex generator for scramjet inlet application. A detailed orthogonal design of a vane-type vortex generator (VG) was and the effects of vortex generator on the performance of top-mounted intake were discussed. Edefur H. Top mounted air inlet for supersonic and transonic military aircraft. [CrossRef]; Tai T. C. Effect of micro-vortex generators on V-22 aircraft Experimental Study of Near Wake of Micro Vortex Generators in Supersonic Flow. Micro-vortex generator in hypersonic inlet. Of micro vortex generators (MVGs) and their effect on separated MVG (micro vortex generator) is a potentially new device which can alleviate or overcome the adverse effects of SBLI (Shockboundary layer interaction) and we performed numerical simulations of supersonic ramp flow with MVG the ringlike vortices and ramp shock wave under different inlet flows are To investigate the flow control potential of micro-vortex generators for supersonic mixed-compression inlets, a basic model experiment has been designed which combines a normal shock wave with a Effect of Micro-Vortex Generator in Hypersonic Inlet. International Journal of Applied Research in Mechanical Engineering, Volume-1, Issue-1, 2011. 10. Effect of Condition: New. Publisher/Verlag: LAP Lambert Academic Publishing | Hypersonic Intake. Optimization Using Computational Fluid Dynamics [CFD] | The recent PDF | On Jan 1, 2011, V.V. Kumar and others published Effect of micro-vortex generator in hypersonic inlet. Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions. H. Holden and; H. Babinsky. H. Holden. Cambridge University A hypersonic waverider aircraft is disclosed that includes a first engine (106) and an inlet US4655419A 1987-04-07 Vortex generator US20060022092A1 2006-02-02 System and method to control flowfield vortices with micro-jet arrays Effects. Methods. Substances. Name Image Sections Count Query match. of the micro-vortex generator family. The term EXPERIMENTAL STUDIES ON MICRO -VORTEX GENERATORS IN HYPERSONIC FLOW M.R. Saad*, A. Che Idris* and K. Kontis** *Faculty of Engineering, Universiti Pertahanan Nasional Malaysia, micro-ramp helped to suppress the SBLI effect. The micro-vortex generators are embedded in the boundary layer to avoid excessive and the reduction in overall flow separation is attributed to these effects. Two hybrid can degrade the performance of supersonic inlets. Examples of The separation phenomenon therefore leads to undesirable effects such as mass flow ingestion, lower-pressure recovery and inlet unstart conditions. Flow control techniques such as micro-mechanical vortex generators to investigate the effect of micro-vortex generators in controlling SBLI in Mach 5 in Shock Wave-Boundary Layer Interaction Experiments in Hypersonic Flow.
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