Date of Award
Fall 1989
Document Type
Thesis
Degree Name
Master of Science (MS)
Department
Mechanical & Aerospace Engineering
Program/Concentration
Mechanical Engineering
Committee Director
Oktay Baysal
Committee Member
Surendra N. Tiwari
Committee Member
James L. Pittman
Call Number for Print
Special Collections; LD4331.E56E54
Abstract
The recent renewal of interest in hypersonic aerodynamics, brought about largely in part due to the development of the National Aerospace Plane (NASP), is resulting in an increased reliance on computational fluid dynamics for flowfield data in this flight regime. The design of the nozzle-afterbody section for a hypersonic transport such as the NASP is currently underway, and is being conducted using both computational fluid dynamics and cold, non-reacting, simulant gas experimental models. In this study, a computational analysis is conducted for the flow through a scramjet nozzle-afterbody test section.
Computations have been performed for a cold gas simulation of a scramjet afterbody flowfield using the Reynolds averaged Navier-Stokes equations. The computations are compared with the results obtained from an experimental study of scramjet module nozzle-afterbody flows. The expansion of a supersonic flow through an internal/external
nozzle-afterbody configuration and its viscous mixing with a hypersonic freestream flow of air is computed using two and three-dimensional upwind, finite volume, Navier-Stokes schemes. The Reynolds stresses are represented by a Baldwin-Lomax algebraic turbulence model with modifications to account for separated flow, multiple wall geometry, and turbulent wake flow. Two-dimensional computations are performed on both fixed and flow adapted grids, and three-dimensional results are computed over a half-span nozzle model on a fixed grid. The results obtained from the adapted grid computations show improved accuracy and resolution, especially in regions where shocks and shear layers occur. Afterbody flowfield results are presented for two-dimensional over-expanded (off design) and under-expanded nozzles, and a three-dimensional spanwise symmetric nozzle. The two-dimensional and three-dimensional nozzle computations compare favorably with experimental results. Furthermore, the results demonstrate that the solutions obtained from the computational fluid dynamics algorithms used in this study, can be used to expand the database for these types of nozzle-afterbody configurations.
Rights
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DOI
10.25777/j8rn-8874
Recommended Citation
Engelund, Walter C..
"Navier-Stokes Analysis of Cold Gas Scramjet Nozzle-Afterbody Flowfields"
(1989). Master of Science (MS), Thesis, Mechanical & Aerospace Engineering, Old Dominion University, DOI: 10.25777/j8rn-8874
https://digitalcommons.odu.edu/mae_etds/484