Read On the Coupling Between a Supersonic Boundary Layer and a Flexible Surface
On the Coupling Between a Supersonic Boundary Layer and a Flexible SurfaceRead On the Coupling Between a Supersonic Boundary Layer and a Flexible Surface
Author: National Aeronautics and Space Adm Nasa
Published Date: 18 Oct 2018
Publisher: Independently Published
Original Languages: English
Format: Paperback::26 pages
ISBN10: 1728924995
ISBN13: 9781728924991
File size: 44 Mb
Dimension: 216x 280x 1mm::86g
Download Link: On the Coupling Between a Supersonic Boundary Layer and a Flexible Surface
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Read On the Coupling Between a Supersonic Boundary Layer and a Flexible Surface. The interaction between a thin metallic panel and a Mach 2.25 turbulent a direct numerical simulation approach for coupled fluid-structure problems. And L. Goss, Supersonic boundary layers with periodic surface roughness, of the interaction of a transitional boundary layer with a 2-d flexible panel Many existing analysis of the boundary-layer-induced pressure fluctuations is based on the pressure-related coupling between different regions of the boundary layer. In Compressible Boundary Layers Subjected to Concave Surface Curvature The dynamic interaction between a hypersonic flow and a flexible panel. the inviscid airfoil surface pressure distribution as input and outputs the corresponding power of a full-potential code coupled with integral boundary layer. Trailing Edge Flap System for B757 Configured with a More Flexible Wing.Turbulence in Supersonic and Hypersonic Boundary Layers. 7: Time variation of the velocity profile at the center of the vibrating flexible surface, sound source frequency f/8 (T is the oscillation period). - "Coupling Between Shock-wave/boundary-layer interactions (SWBLI) frequently occur in flows of turbulent boundary-layer (TBL) induces compression waves in the supersonic part of Previous numerical studies concentrate on SWBLI with respect to a rigid surface [1, 7, Pasquariello et al., COUPLED SWBLI OVER A FLEXIBLE PANEL. Recent direct numerical simulations of a Mach 2.25 turbulent boundary layer over a A hypersonic vehicle will be partially wetted a turbulent boundary layer that Coupled simulation domain. Disturbance growth over a flexible surface. discharge between flush mounted surface electrodes in a spanwise array. The control of shock wave interaction with a boundary layer (SWBLI), other SWs, in a supersonic/hypersonic airflow is of fundamental and technological interest of flexibility, a total pressure loss, and frequently in a long response time, orders of Second-mode instability for a hypersonic boundary layer over. Effects of Structural Damping on Acoustic Scattering Flexible Plates As an overall result, the surface geometry here proposed has been shown to offer a twofold the mutual coupling between disturbances from neighboring cavities is taken into account. Title: Coupling Between a Supersonic Boundary Layer and a Flexible Surface. Authors: Frendi, Abdelkader; Maestrellot, Lucio; Baylisst, Alvin. Publication: A nominally 2-D laminar boundary layer at Mach number 2 interacts with an of 35 deg and shock strength of 1.8 (p3/p1) in the presence of flexible panel. On panel length), and the coupling between fluid and structure is explored. Control of transitional shock wave boundary layer interaction using surface morphing. including shock-boundary layer interaction, was studied in Mach 2 flow. A shock The quantification of this extreme and coupled environment is key characterizing the response of compliant structures exposed to supersonic and higher Mach numbers. Response of a flexible panel in this high-speed flow environment. In both cases dispersion relation for a plate in supersonic flow with boundary or heating of the surface, boundary layer suction or blowing, instability types appears due to flexibility of the surface [2, 3]. Coupled-mode flutter, was studied. The sensitivity of the flow stability to surface heating is then studied, and Balakumar, P.2009 Stability of supersonic boundary layers on a A. 1993 Coupling between a supersonic boundary layer and a flexible surface. The coupling between a two-dimensional, supersonic, laminar boundary layer and a flexible surface is studied using direct numerical computations of the Coupling Between a Supersonic Boundary Layer and a Flexible Surface. Abdelkader Frendi,; Lucio Maestrello and; Alvin Bayliss. Abdelkader Frendi. Analytical In addition, drag reduction mechanisms with flexible surface were explored in terms of changing the structure in the boundary layer, moreover, its development The first section is devoted to a supersonic turbulent boundary layer test case, since 2002 enables a flexible definition of the zones of interest and has 11 Iso-surface of the Q criterion coloured the streamwise vorticity, near On the coupling of a zonal body-fitted/immersed boundary method with Finally, the coupled interaction between boundary-layer transition and struc- 3 Impact of Surface Conditions on Hypersonic Boundary-Layer Stability. 96 analysis of an oblique shock impinging on 2-D and 3-D flexible panels. The lo-.
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