Journal of Space Science and Technology

Journal of Space Science and Technology

Boundary Layer Transition and Re-Laminarization in the Nozzle of a Shock Tunnel – a Numerical Study

Document Type : Original Research Paper

Authors
1 Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran
2 Technical University of Denmark, Lyngby, Denmark
Abstract
The boundary layer behavior in hypersonic nozzle of a shock tunnel has been investigated by means of the computational fluid dynamics simulations. The state of boundary layer at the nozzle outlet can highly affect the downstream flow passing around the test model in the shock tunnel test section. The formation of shock and expansion wave systems towards the downstream diaphragm and the reflection and expansion waves towards the upstream shock tube were well-simulated after the diaphragm rupture. Focusing on the transitional boundary layer simulation, results of the optimal nozzle's steady-state flow indicate that the boundary layer enters the throat region, undergoes a phase transition, and then returns to a laminar state due to re-acceleration. The turbulence intensity in this region, coupled with the width of the transition zone, increases with higher upstream stagnation pressure. Furthermore, simulation of the unsteady starting flow shows that the passage time of unsteady waves and the quasi-steady region, have good agreement with the experimental results.
Keywords
Subjects

Article Title Persian

Boundary Layer Transition and Re-Laminarization in the Nozzle of a Shock Tunnel – a Numerical Study

Authors Persian

شاهد ملکی پور 1
ایمان بهمن جهرمی 1
میثم محمدی امین 2
1 پژوهشگاه هوافضا، وزارت علوم، تحقیقات و فناوری، تهران، ایران
2 دانشگاه فنی دانمارک، لینگبی، دانمارک
Abstract Persian

The boundary layer behavior in hypersonic nozzle of a shock tunnel has been investigated by means of the computational fluid dynamics simulations. The state of boundary layer at the nozzle outlet can highly affect the downstream flow passing around the test model in the shock tunnel test section. The formation of shock and expansion wave systems towards the downstream diaphragm and the reflection and expansion waves towards the upstream shock tube were well-simulated after the diaphragm rupture. Focusing on the transitional boundary layer simulation, results of the optimal nozzle's steady-state flow indicate that the boundary layer enters the throat region, undergoes a phase transition, and then returns to a laminar state due to re-acceleration. The turbulence intensity in this region, coupled with the width of the transition zone, increases with higher upstream stagnation pressure. Furthermore, simulation of the unsteady starting flow shows that the passage time of unsteady waves and the quasi-steady region, have good agreement with the experimental results.

Keywords Persian

Boundary layer transition
Computational fluid dynamics
Hypersonic nozzle flow
Nozzle starting flow
Shock tunnel
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Volume 18, Special Issue (S1)
In English
2025
Pages 52-59

  • Receive Date 21 January 2025
  • Revise Date 07 February 2025
  • Accept Date 16 February 2025
  • First Publish Date 23 February 2025