Volume 18, Issue 9 (2018)                   Modares Mechanical Engineering 2018, 18(9): 199-206 | Back to browse issues page

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Malekipour S, Ebrahimi M. Multiobjective Design Optimization of a Mach 6 Hypersonic Nozzle of a Shock Tunnel. Modares Mechanical Engineering. 2018; 18 (9) :199-206
URL: http://mme.modares.ac.ir/article-15-15187-en.html
1- PhD Candidate / Aerospace Research Institute
2- Faculty Member/Aerospace Research Institute
Abstract:   (2054 Views)
In this paper, a systematic approach is considered to Design an optimal hypersonic Nozzle of a shock tunnel. After assigning the requirements and accomplishment of conceptual and preliminary design phases, a modern optimization strategy based on genetic algorithm and a CFD solver has been used to fine tune the nozzle convergent divergent contour. In this way, parameterization of the overall nozzle contour was done with a few control points and a Bezier curve. This arrangement showed a good flexibility to generate appropriate curves for nozzle shape. Design objectives were evaluated with a N-S viscous solver with a two equation turbulence model. Three objective functions were scalerized in a term with summation of weighted parameters: minimum total pressure loss, Mach number uniform distribution along test section and minimum axial flow deviation. A number of geometrical and physical constraints such as nozzle length, throat area, inlet and outlet diameters and inlet boundary conditions were also considered and finally, an optimized nozzle contour showed a significant improvement of about 3% in quality of the Mach 6 flow in the test section.
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Article Type: Research Article | Subject: Aerospace Structures
Received: 2018/03/7 | Accepted: 2018/09/25 | Published: 2018/09/25

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