Optimization of an axisymmetric mach 6 reflected-shock tunnel nozzle at flight enthalpy

A. Hameed, M. A. Mustafa, D. Shekhtman, N. J. Parziale

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

1 Scopus citations

Abstract

In this work, we present an optimization process for the design of converging-diverging nozzle contours. The process is a brute-force algorithm that runs CFD simulations for various contours until the one with the most uniform flow properties is obtained. The contour is described using a Bezier curve, with control points serving as the independent variables in the optimization process. The function that is minimized is a penalty function that characterizes the non-uniformity of the flow properties. The optimization is carried out in three steps: contour definition, inviscid optimization, and viscous optimization. The inviscid optimization is performed with a coarse grid and a CFD model with no viscosity or turbulence. This serves to rapidly design a contour that is close to the desired performance. Using the result of the inviscid optimization as a starting point, further refinement is carried out in the viscous optimization, with a finer grid and a CFD model that accounts for all relevant physical phenomena. Different CFD solvers are used at each step, and results are presented for the design of a Mach 6 nozzle for the Stevens Shock Tunnel.

Original languageEnglish
Title of host publicationAIAA Scitech 2021 Forum
Pages1-15
Number of pages15
StatePublished - 2021
EventAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021 - Virtual, Online
Duration: 11 Jan 202115 Jan 2021

Publication series

NameAIAA Scitech 2021 Forum

Conference

ConferenceAIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
CityVirtual, Online
Period11/01/2115/01/21

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