High Order Large Eddy Simulation for Shock-Boundary Layer Interaction Control by a Micro-ramp Vortex Generator (Frontiers in Aerospace Science)

Liu, Chaoqun/ Li, Qin/ Yan, Yonghua/ Yang, Yong/ Yang, Guang/ Dong, Xiangrui

ISBN 10: 1681085984 / ISBN 13: 9781681085982

Verlag: Bentham Science Publishers, 2017

Beschreibung

320 pages. 10.00x7.00x0.76 inches. In Stock.

Bestandsnummer des Verkäufers zk1681085984

Bibliografische Details

• Titel: High Order Large Eddy Simulation for Shock-Boundary Layer Interaction Control by a Micro-ramp Vortex Generator (Frontiers in Aerospace Science)
• Verlag: Bentham Science Publishers
• Erscheinungsjahr: 2017
• Sprache: Englisch
• ISBN-10: 1681085984
• ISBN-13: 9781681085982
• Einband: Paperback
• Zustand: Brand New
• Gewicht: 0,7 Kilogramm

Über diesen Titel

Inhaltsangabe

This volume presents an implicitly implemented large eddy simulation (ILES) by using the fifth order bandwidth-optimized WENO scheme. The chosen method is applied to make comprehensive studies on ramp flows with and without control at Mach 2.5 and Re=5760. Flow control in the form of microramp vortex generators (MVG) is applied. The results show that a MVG can distinctly reduce the separation zone at the ramp corner and lower the boundary layer shape factor under simulated conditions. A series of new findings about the MVG-ramp flow are obtained, including structures relevant to surface pressure, three-dimensional structures of the re-compression shock waves, a complete surface separation pattern, momentum deficit and a new secondary vortex system. A new mechanism of shock-boundary layer interaction control by MVG associated with a series of vortex rings is also presented. Vortex rings strongly interact with air flow and play an important role in the separation zone reduction. Additionally, readers will learn about the governing equation, boundary condition, high quality grid generation, high order shock capturing scheme and DNS inflow condition in detail. This volume will, therefore, serve as a useful reference for aerospace researchers using LES methods to study shock boundary layer interaction and supersonic flow control.