...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of Aircraft >Evaluation of Wall-Interference Correction Method Using Numerical Analysis and Porous Wall Model
【24h】

Evaluation of Wall-Interference Correction Method Using Numerical Analysis and Porous Wall Model

机译：基于数值分析和多孔壁模型的壁面干涉校正方法评估

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

Evaluation of the conventional linear wall-interference correction method is conducted using flows around a two-dimensional airfoil in a wind tunnel computed by computational fluid dynamics and a porous wall model. First, the computational results are validated by comparison with wind-tunnel test measurements. Then, the wall-interference effect is discussed using these results. Porous walls are effective for reducing blockage, which change the Mach number around the airfoil. However, high wall porosity causes large downwash, which changes the flow angle. In this paper, Mokry's method, which is one of the linear wall-interference correction methods, is evaluated quantitatively using computational fluid dynamics. Computational result with wind-tunnel walls are corrected by Mokry's method, and the corrected result is compared with the one without wind-tunnel walls. Mokry's method shows high accuracy in subsonic and no-stall conditions, which satisfy the requirement of the small-perturbation potential equation. Its accuracy is also high even if the model is large relative to the wind-tunnel size. However, an error of about 10 drag counts is caused due to a shock wave in transonic flow conditions, and accuracy rapidly degrades around the stall condition, where an error exceeding 100 counts is caused by flow separation.
机译：使用通过计算流体动力学和多孔壁模型计算出的风洞中二维翼型周围的流动，对常规线性壁干扰校正方法进行评估。首先，通过与风洞测试测量结果进行比较来验证计算结果。然后，利用这些结果来讨论壁干扰效应。多孔壁对于减少堵塞是有效的，该堵塞改变了翼型周围的马赫数。但是，高的壁孔率会导致大量的冲洗，从而改变流动角度。本文采用计算流体动力学定量评估了莫克瑞方法，该方法是线性壁干扰校正方法之一。用莫克里的方法校正了具有风洞壁的计算结果，并将校正后的结果与没有风洞壁的计算结果进行了比较。 Mokry的方法在亚音速和无失速条件下显示出很高的精度，可以满足小扰动势方程的要求。即使模型相对于风洞尺寸较大，其准确性也很高。但是，由于跨音速流动条件下的冲击波会导致大约10个阻力计数的误差，并且在失速条件附近精度会迅速下降，在该失速条件下，流动分离会导致超过100个计数的误差。

著录项

  • 来源
    《Journal of Aircraft》 |2015年第1期|226-234|共9页
  • 作者

    Taisuke Nambu; Atsushi Hashimoto; Makoto Ueno; Keiichi Murakami; Tetsuya Sato;

  • 作者单位

    Waseda University, Tokyo 169-8555, Japan;

    Japan Aerospace Exploration Agency, Tokyo 182-8522, Japan;

    Japan Aerospace Exploration Agency, Tokyo 182-8522, Japan;

    Japan Aerospace Exploration Agency, Tokyo 182-8522, Japan;

    Waseda University, Tokyo 169-8555, Japan;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

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