Study on Performance of Detonation-Driven Shock Tube

Yamanaka, Akio; Ariga, Yosuke; Obara, Tetsuro; Cai, Pin; Ohyagi, Shigeharu

doi:10.1299/jsmeb.45.425

Search citation statements

Order By: Relevance

Paper Sections

Select...

B Shock Tube Conditions1

Introduction1

Citation Types

Supporting

Mentioning

Contrasting

Year Published

2004

2022

Publication Types

Select...

Article4

Other1

Relationship

Self Cite0

Independent5

Authors

Journals

Cited by 5 publications

(2 citation statements)

References 4 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The driving capacity was considered to be strongly influenced by the rupturing condition of the diaphragm placed between the driver section and shock tube [14]. Using the shock tube theory, the pressure ratio of P4 to P1 can be calculated by the following equation.…”

Section: B Shock Tube Conditionsmentioning

confidence: 99%

Performance of a detonation driven shock tunnel

Li¹,

Wang²,

Zhao³

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

View full text Add to dashboard Cite

Section: B Shock Tube Conditionsmentioning

confidence: 99%

Performance of a detonation driven shock tunnel

Li¹,

Wang²,

Zhao³

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

View full text Add to dashboard Cite

“…A high-enthalpy shock tunnel is a type of pulse tunnel that produces high-enthalpy flow by compressed air with strong shock waves [3,4]. It is widely used in hypersonic fields, such as Earth reentry, planet entry, hypersonic aircraft, scramjet, etc.…”

Section: Introductionmentioning

confidence: 99%

Numerical and Experimental Study on the Duration of Nozzle Starting of the Reflected High-Enthalpy Shock Tunnel

Wang

et al. 2022

Applied Sciences

View full text Add to dashboard Cite

The starting process of the flow in the nozzle of the JF-14 shock tunnel (1.6 m in length, 500 mm in outlet diameter) in the State Key Laboratory of High Temperature Gas Dynamics is analyzed by calculation and experiment. Two key factors which directly affect the duration of the nozzle starting are the velocity of the expansion wave and the low-velocity zone generated by the interaction between the secondary shock wave and boundary layer on the wall surface. In the process of the nozzle starting, the flow field stabilizes at the center of the nozzle outlet first, and then gradually stabilizes along the radius direction, thus defining the central startup and complete startup of the nozzle. It is found that there is a critical initial pressure. When the initial pressure is lower than the critical pressure, the airflow can reach stability in the nozzle outlet center with the shortest time, otherwise, the time required is much longer. The time required for the airflow to stabilize in the whole outlet section is mainly affected by the size of the low-velocity zone. It is also found that only at a very low initial pressure can the airflow simultaneously reach stability at the entire outlet of the nozzle.

show abstract

Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode

Wang

Luo

et al. 2020

Chinese Journal of Aeronautics

View full text Add to dashboard Cite

Study on Performance of Detonation-Driven Shock Tube

Cited by 5 publications

References 4 publications

Performance of a detonation driven shock tunnel

Performance of a detonation driven shock tunnel

Numerical and Experimental Study on the Duration of Nozzle Starting of the Reflected High-Enthalpy Shock Tunnel

Investigation of dual ignition for a detonation-driven shock tunnel in forward driving mode

Contact Info

Product

Resources

About