TY - GEN
T1 - Optimization of an axisymmetric mach 6 reflected-shock tunnel nozzle at flight enthalpy
AU - Hameed, A.
AU - Mustafa, M. A.
AU - Shekhtman, D.
AU - Parziale, N. J.
N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - 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.
AB - 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.
UR - http://www.scopus.com/inward/record.url?scp=85100318476&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85100318476&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85100318476
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 15
BT - AIAA Scitech 2021 Forum
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -