Preliminary study on transonic flow characteristics of a high-pressure capturing wing configuration

WANG Haoxiang; LI Guangli; XU Yingzhou; CUI Kai

doi:10.7638/kqdlxxb-2019.0075

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Preliminary study on transonic flow characteristics of a high-pressure capturing wing configuration

更新时间：2026-05-28

- Preliminary study on transonic flow characteristics of a high-pressure capturing wing configuration
- Vol. 38, Issue 3, Pages: 441-447(2020)
- 作者机构：
  
  1. 中国科学院力学研究所高温气动国家重点实验室,北京,100190
  2. 中国科学院大学工程科学学院,北京,100049
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2019.0075
  CLC： V211.3;V224
- Published：2020
- 稿件说明：
移动端阅览
王浩祥, 李广利, 徐应洲, 崔凯. 高压捕获翼构型跨声速流动特性初步研究[J]. 空气动力学学报, 2020, 38(3): 441-447.

WANG Haoxiang, LI Guangli, XU Yingzhou, et al. Preliminary study on transonic flow characteristics of a high-pressure capturing wing configuration[J]. 2020, 38(3): 441-447.
王浩祥, 李广利, 徐应洲, 崔凯. 高压捕获翼构型跨声速流动特性初步研究[J]. 空气动力学学报, 2020, 38(3): 441-447. DOI： 10.7638/kqdlxxb-2019.0075.

WANG Haoxiang, LI Guangli, XU Yingzhou, et al. Preliminary study on transonic flow characteristics of a high-pressure capturing wing configuration[J]. 2020, 38(3): 441-447. DOI： 10.7638/kqdlxxb-2019.0075.

摘要

高压捕获翼是一种可以在高超声速条件下同时获得高升阻比、高容积率和高升力系数的新型布局概念。为初步分析该类新型布局的宽速域气动特性，以一种圆锥-圆台体组合高压捕获翼原理性构型为计算模型，以典型跨声速条件（马赫数0.92、0°攻角）为计算工况，进行了计算和分析。流场分析结果表明，在跨声速流动条件下，机体与高压捕获翼之间存在比较强烈的气动干扰，且干扰的强烈程度与高压捕获翼-机体间的垂向距离大小直接相关。与不带捕获翼的参考构型相比，增加捕获翼会导致机体尾部分离区范围增大，并在机体与捕获翼之间的开放通道内形成类似于变截面收缩管的流动，致使沿流向方向出现了明显的激波串，进而导致捕获翼下表面壁面压力出现较为明显的波动。同时，由于机体和捕获翼间的垂直距离沿展向方向逐渐增加，导致该波动在对称面附近最为剧烈，然后随展向位置逐渐增加，压力波动逐渐减弱。

Abstract

High-pressure capturing wing configurations (HCW) are a family of new concepts which are proposed to meet the design requirements of high volumetric efficiency

high lift coefficient

and high lift-to-drag ratio for hypersonic flight vehicles. In order to investigate the flow characteristics as well as the aerodynamic performance of a typical HCW configuration in a wide-speed range

a preliminary study was conducted in this paper. A cone-truncated cone combination geometry is taken as the simplified computational model. Afterwards

a computational fluid dynamics study was carried out under the freestream flow condition of Mach number 0.92 and 0° angle of attack. Besides

a comparison study was conducted on the basis of the results between the configurations with and without the HCW. Numerical results show that there exists a strong aerodynamic interference between the body and the HCW in the transonic flow regime. The results demonstrated that the area of the flow separation section near the tail part increases significantly as a result of appending the HCW. In the opening channel between the fuselage and the HCW

a shock train appears clearly along the flow direction. This phenomenon leads to that the wall pressure on the lower surface of the HCW presents a significant oscillation. Furthermore

the most obvious oscillation appears in the region near the symmetrical plane

and then it gradually fades with the increase of the spanwise distance.

关键词

Keywords

references

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