• 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of aerospace engineering >Toward a Low Noise Shock Tunnel Facility via Multiobjective Optimization of Hypersonic Nozzle
【24h】

Toward a Low Noise Shock Tunnel Facility via Multiobjective Optimization of Hypersonic Nozzle

机译：通过多层喷嘴的多目标优化朝着低噪声冲击隧道设施

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

In this paper, a systematic approach is considered for the development of a low noise shock tunnel facility. For this purpose, an optimal hypersonic nozzle and test section configuration is presented along with a previously developed low noise shock tube design. In hypersonic experimental studies, one of the most important requirements is a low noise test section with a high-quality uniform flow. The main sources of perturbations are acoustic fluctuations that occur through the turbulent boundary layer and Mach line fluctuations with the passage of turbulent flow through the hypersonic nozzle. The fluctuations are correlated to wall boundary layer thickness, radiated disturbances, and their concentration on the nozzle axis. These parameters can be indirectly controlled via definition of three weighted objective functions-minimum total pressure loss, uniform Mach number distribution, and minimum axial flow deviation-combined to attain the final scalar objective function. Then, a modern optimization strategy is implemented based on a genetic algorithm, parallel CFD solver, and the requirements and constraints from conceptual and preliminary design. In this way, parameterization of the overall nozzle contour is performed with a few control points and Bezier curve that showed good flexibility for generating appropriate nozzle curves. Design objectives are evaluated using a Navier-Stokes solver with a k-omega turbulence model. Various geometrical and physical constraints such as nozzle length, throat area, inlet and outlet diameters, and inlet boundary conditions are considered. It is concluded that the proposed strategy for tuning the nozzle convergent-divergent contour minimizes the boundary layer effects and shows a significant improvement in the quality of test section flow and consequently a reduction in the noise level of shock tunnel test facility. (C) 2021 American Society of Civil Engineers.
机译：在本文中，考虑了一种系统方法，用于开发低噪声冲击隧道设施。为此目的，提出了一种最佳的超声喷嘴和测试部分配置以及先前显影的低噪声冲击管设计。在超音速实验研究中，最重要的要求之一是低噪声测试部分，具有高质量的均匀流。扰动的主要来源是通过湍流边界层和马赫线波动发生的声波波动，通过超声波喷嘴通过湍流的通过。波动与壁边界层厚度，辐射扰动及其在喷嘴轴上的浓度相关。这些参数可以通过定义间接控制三个加权物镜函数 - 最小总压力损失，均匀的马赫数分布和最小轴向流偏差组合以获得最终标量的目标函数。然后，基于遗传算法，并行CFD求解器以及来自概念和初步设计的要求和约束来实现现代优化策略。以这种方式，通过少数控制点和贝塞尔曲线执行整个喷嘴轮廓的参数化，该控制点和Bezier曲线显示出用于产生适当的喷嘴曲线的良好柔韧性。使用带有K-Omega湍流模型的Navier-Stokes求解器来评估设计目标。考虑各种几何和物理限制，例如喷嘴长度，喉部区域，入口和出口直径和入口边界条件。得出结论，提出的调整喷嘴会聚 - 发散轮廓的策略最小化边界层效应，并显示出测试截面流量的质量的显着改善，从而降低了冲击隧道测试设施的噪声水平。 （c）2021年美国土木工程师协会。

著录项

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号