Nozzle design optimization for axisymmetric scramjets by using surrogate-assisted evolutionary algorithms

Hideaki Ogawa, Russell R. Boyce

研究成果: ジャーナルへの寄稿学術誌査読

43 被引用数 (Scopus)

抄録

Scramjet propulsion is a promising hypersonic airbreathing technology that offers the potential for efficient and flexible access to space and high-speed atmospheric transport. Robust nozzle design over a range of operating conditions is of critical importance for successful scramjet operation. In this paper, shape optimization has been performed with surrogate-assisted evolutionary algorithms to maximize the thrust generated by an axisymmetric scramjet nozzle configuration, including the base flow and external surface for cruise conditions at Mach 8 at two altitudes with and without fuel. The optimization results have been examined in a coupled numerical/analytical approach in order to identify the key design factors and investigate the effects of design parameters. It has been found that the optimum nozzle geometries are characterized by bell-type shapes for the fuel-on conditions, whereas the optima for the fuel-off case feature nearly conical shapes. Their robustness in thrust production has been demonstrated by cross- referencing the optimum geometries at off-design altitudes. The nozzle length and radius have been found to be the most influential parameters in all considered conditions, with their optimum values determined based on the balance between inviscid and viscous force components, whereas the other parameters have minor impact on the total axial force.

本文言語英語
ページ(範囲)1324-1338
ページ数15
ジャーナルJournal of Propulsion and Power
28
6
DOI
出版ステータス出版済み - 2012
外部発表はい

!!!All Science Journal Classification (ASJC) codes

  • 航空宇宙工学
  • 燃料技術
  • 機械工学
  • 宇宙惑星科学

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