Numerical simulation on formation process of high-enthalpy flow fields in hydrogen-driven shock tunnels

WU Xuanyu; KONG Xiaoping; SHEN Zhihao; XU Hailun

doi:10.7638/kqdlxxb-2024.0105

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Numerical simulation on formation process of high-enthalpy flow fields in hydrogen-driven shock tunnels

更新时间：2026-05-28

- Numerical simulation on formation process of high-enthalpy flow fields in hydrogen-driven shock tunnels
- Vol. 43, Issue 12, Pages: 81-89(2025)
- 作者机构：
  
  1. 西南科技大学土木工程与建筑学院,绵阳,621010
  2. 飞行器流体物理全国重点实验室,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0105
  CLC： V211.73
- Published：2025
- 稿件说明：
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吴轩宇, 孔小平, 慎志豪, 等. 氢气驱动激波风洞高焓流场建立过程的数值模拟研究[J]. 空气动力学学报, 2025, 43(12): 81−89.

WU Xuanyu, KONG Xiaoping, SHEN Zhihao, et al. Numerical simulation on formation process of high-enthalpy flow fields in hydrogen-driven shock tunnels[J]. 2025, 43(12): 81-89.
吴轩宇, 孔小平, 慎志豪, 等. 氢气驱动激波风洞高焓流场建立过程的数值模拟研究[J]. 空气动力学学报, 2025, 43(12): 81−89. DOI： 10.7638/kqdlxxb-2024.0105

WU Xuanyu, KONG Xiaoping, SHEN Zhihao, et al. Numerical simulation on formation process of high-enthalpy flow fields in hydrogen-driven shock tunnels[J]. 2025, 43(12): 81-89. DOI： 10.7638/kqdlxxb-2024.0105.

摘要

为了更全面地掌握氢气驱动激波风洞中高焓流场的建立过程，本文通过采用二阶空间精度和双时间步长的隐式算法对其进行了数值模拟研究，涵盖了从风洞起动到喷管出口稳定流场形成的整个阶段。模拟结果显示：在高压区氢气50 MPa、低压区空气100 kPa、温度均为300 K的情况下，8.54 ms时二道隔膜破裂，而在10.20 ms时喷管入口的气流压力升至29.8 MPa，温度达到

3500

K，并维持了6.80 ms；激波在喉道处经历了“入射激波-斜激波-激波串-弓形激波-λ激波”的过程；气流在喷管下游形成主激波，随后产生二次激波，两者共同向下游移动，最终在13.00 ms时在喷管内形成了稳定的流场，并持续了2.00 ms；稳定流场的核心区域马赫数约为9.1，静压约为900 kPa，静温约为260 K，喷管出口的均匀区域直径约为840 mm。本研究不仅增进了对激波风洞高焓流场建立过程的理解，而且对提升地面模拟试验设备的运行能力具有重要意义，满足了高速飞行器发展的需求。

Abstract

To comprehensively investigate the formation of high-enthalpy flow fields in hydrogen-driven shock tunnels

this study conducted an in-depth numerical simulation using an implicit algorithm with second-order spatial accuracy and dual-time stepping. The simulation covered the entire evolution from tunnel initiation to the establishment of a stable flow field at the nozzle exit. Results demonstrate that under initial conditions of 50 MPa hydrogen in the high-pressure section and 100 kPa air in the low-press

ure section (both at 300 K)

the double diaphragms ruptured at 8.54 ms. By 10.20 ms

the flow pressure at the nozzle inlet reached 29.8 MPa with a temperature of

3500

and remained stable for 6.80 ms. The shock wave evolution in the throat region exhibited a characteristic sequence: incident shock; oblique shock; shock train; bow shock; lambda shock. In the downstream nozzle section

a primary shock wave formed fint

followed by a secondary shock. These two shocks propagated cooperatively downstream

ultimately establishing a stable flow field at 13.00 ms

which persisted for 2.00 ms. The stabilized flow field exhibited a core region with a Mach number of about 9.1

static pressure of about 900 kPa

and static temperature of about 260 K

while a uniform flow zone with a diameter of approximately 840 mm was achieved at the nozzle exit. This research enhances the fundamental understanding of high-enthalpy flow dynamics in shock tunnels and provides critical insights for optimizing ground-based hypersonic testing facilities to meet the demands of advanced aerospace vehicle development.

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references

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