NDLI: Numerical investigation of flow in an over-expanded nozzle with porous surfaces

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Numerical investigation of flow in an over-expanded nozzle with porous surfaces

Content Provider	NASA Technical Reports Server (NTRS)
Author	Abdol-Hamid, K. S. Elmiligui, Alaa Hunter, Craig A.
Copyright Year	2005
Description	A new porous condition has been implemented in the PAB3D solver for simulating the flow over porous surfaces. The newly-added boundary condition is utilized to compute the flow field of a non-axisymmetric, convergent-divergent nozzle incorporating porous cavities for shock-boundary layer interaction control. The nozzle has an expansion ratio (exit area/throat area) of 1.797 and a design nozzle pressure ratio of 8.78. The flow fields for a baseline nozzle (no porosity) and for a nozzle with porous surfaces (10% porosity ratio) are computed for NPR varying from 2.01 to 9.54. Computational model results indicate that the over-expanded nozzle flow was dominated by shock-induced boundary-layer separation. Porous configurations were capable of controlling off-design separation in the nozzle by encouraging stable separation of the exhaust flow. Computational simulation results, wall centerline pressure, mach contours, and thrust efficiency ratio are presented and discussed. Computed results are in excellent agreement with experimental data.
File Size	749181
Page Count	19
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_20050192463
Archival Resource Key	ark:/13960/t3tt9kj6v
Language	English
Publisher Date	2005-01-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Thermodynamics Boundary Layer Separation Nozzle Geometry Nozzle Flow Flow Distribution Shock Wave Interaction Convergent-divergent Nozzles Boundary Conditions Porous Boundary Layer Control Porosity Computer Programs Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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