重气体介质中超临界翼型跨声速流动特性

查俊; 曾开春; 寇西平; 杨兴华; 张汇卓

doi:10.13224/j.cnki.jasp.20200490

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重气体介质中超临界翼型跨声速流动特性

气动热力学与总体设计 | 更新时间：2025-04-07

- 重气体介质中超临界翼型跨声速流动特性
- Transonic flow characteristics of supercritical airfoil in heavy gas medium
- 航空动力学报 2021年36卷第9期页码：1894-1905
- 作者机构：
  
  1.中国空气动力研究与发展中心高速空气动力研究所，四川绵阳 621000
  2.西北工业大学航空学院，西安 710072
- 作者简介：
  
  查俊（1984-），男，工程师，硕士，主要从事飞行器气动弹性力学研究。
  寇西平（1987-），男，工程师，博士，主要从事飞行器气动弹性力学研究。E-mail：kouxiping@cardc.cc
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20200490
  中图分类号：
- 稿件说明：
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查俊, 曾开春, 寇西平, 等. 重气体介质中超临界翼型跨声速流动特性[J]. 航空动力学报, 2021,36(9):1894-1905.

Jun ZHA, Kaichun ZENG, Xiping KOU, et al. Transonic flow characteristics of supercritical airfoil in heavy gas medium[J]. Journal of Aerospace Power, 2021, 36(9): 1894-1905.
查俊, 曾开春, 寇西平, 等. 重气体介质中超临界翼型跨声速流动特性[J]. 航空动力学报, 2021,36(9):1894-1905. DOI： 10.13224/j.cnki.jasp.20200490.

Jun ZHA, Kaichun ZENG, Xiping KOU, et al. Transonic flow characteristics of supercritical airfoil in heavy gas medium[J]. Journal of Aerospace Power, 2021, 36(9): 1894-1905. DOI： 10.13224/j.cnki.jasp.20200490.

摘要

采用Peng⁃Robinson非理想气体状态方程模拟重气体介质的热力学特性，并与雷诺平均Navier⁃Stokes方程结合，形成封闭的重气体介质流动模型。针对超临界翼型流动问题，利用LU⁃SGS（lower⁃upper symmetric Gauss⁃Seidel）隐式时间推进格式和有限体积法，分别求解空气介质和重气体介质下的流动特性。数值模拟结果表明：在跨声速条件下重气体介质中超临界翼型的升阻力增大、超声速区域表面负压增加、边界层位移厚度减小、激波后移、表面摩擦阻力明显增大、后缘流动分离推迟。该研究为后续重气体介质中飞行器颤振特性研究及修正方法的发展提供了基础支持。

Abstract

The Peng⁃Robinson non⁃ideal gas state equation was used to simulate the thermodynamic characteristics of the heavy gas medium，and to form a closed flow model for heavy gas medium by combining with the Reynolds average Navier⁃Stokes equations.The LU⁃SGS （lower⁃upper symmetric Gauss⁃Seidel） implicit time⁃marching scheme and the finite volume method were used to simulate the flow over a supercritical airfoil in air and heavy gas medium respectively.Numerical results showed that the lift and drag of supercritical airfoil increased，the surface negative pressure in supersonic region increased，the displacement thickness of boundary layer decreased，the shock wave moved backward，the skin friction increased significantly，and the trailing edge flow separation delayed under transonic conditions.This study provides a basic support for the subsequent research on flutter characteristics of aircrafts in heavy gas medium and the development of correction methods.

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