Visualization of developing high temperature supersonic impulse jet induced by blast wave simulator

Mizukaki, Toshiharu

doi:10.1007/bf03181808

Cited by 4 publications

(2 citation statements)

References 13 publications

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“…A large number of experimental studies of the muzzle flow field have been carried out to test the wave system structure, temperature, velocity and pressure of the transient flow field. However, the evolution mechanism of the complex muzzle flow field cannot be described in detail due to the limitations of the experimental methods [1,2]. Following advances in computer performance and high precision algorithms, numerical studies on the complex muzzle flow field have improved a lot [3,4].…”

Section: Introductionmentioning

confidence: 99%

Modeling and Simulation of Back Blast Flow Field of a Recoilless Gun Launching in Finite Space

Cao¹,

Zhang²,

Li³

et al. 2017

dtmse

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A recoilless gun is a kind of weapon equipment for individual soldier and its back blast flow has certain influence on the shooter during the launch process. In order to study the launch safety of a recoilless gun firing in a finite space of 2.5×2.5×2m, numerical simulation of the back blast flow field was carried out based on the three-dimensional unsteady viscous compressible N-S equations. The result shows that a complex reflected shock wave is formed due to the reflection of the wall behind the nozzle. The reflected shock wave represents reciprocating motion in the finite space and its intensity is much higher than that of the initial shock wave. Critical damage will be imposed on the shooter if no safeguard procedure is adopted. The high temperature gas flow may ignite the inflammable gases in the finite space and cause secondary damage. The research results are significant for understanding the characteristics of the back blast flow of the recoilless gun launching in the finite space, predicting and taking effective action to reduce the damage on the shooter.

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Section: Introductionmentioning

confidence: 99%

Modeling and Simulation of Back Blast Flow Field of a Recoilless Gun Launching in Finite Space

Cao¹,

Zhang²,

Li³

et al. 2017

dtmse

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“…Because of its vigorous action, it is not easy to measure the flow ejected from vent-holes of a fill-hose using conventional flow measurement methods. Optical interferometers or LDV system can be applicable to these flows (Mizukaki, 2007). However, the flow information to be obtained would be qualitatively visualized flow images or point-wise data at several measurement locations.…”

Section: Introductionmentioning

confidence: 99%

Dynamic PIV measurement of a high-speed flow issuing from vent-holes of a curtain-type airbag

Lee

Jang

Choi

et al. 2008

J Vis

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A curtain-type airbag is a safety device designed to protect passengers from the side collisions of a car. The curtain-type airbag system consists of an inflator, a fill-hose, and a curtain-airbag. The fill-hose is a passageway and distributor of the exploded gases from the inflator to the airbag through vent-holes. Although the design of vent-holes is important for proper deployment of the airbag, it is very difficult to measure the exceedingly high speed flow issuing from the vent-holes by using conventional measurement methods. In this study, we employed a dynamic PIV technique to measure the temporal evolution of instantaneous velocity fields of the flow ejecting from the vent-holes. From the velocity field data measured at a frame rate of 2000 fps, the temporal variation of the volume flux from vent-holes was also evaluated for the diagnosis of airbag performance. The flows ejecting from the vent-holes showed high velocity fluctuations, and the maximum velocity was about 480 m/s. The instantaneous velocity fields in the initial stage showed a swaying motion of a high-speed jet. The accumulated volume flux from the vent-holes was also compared at each vent-hole region.

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Detached shock waves around cylinders flying at mach number ranging from 1 to 2

Mizukaki

2008

J Vis

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Using a ballistic range with a small single-stage powder gun, characteristics of detached shock waves around cylindrical projectiles were investigated. The detaches shock waves were analyzed quantitatively by visualization method. The projectiles were made of steel, with a diameter of 5.56 mm and with a mass of 1.77 g. The projectiles were ejected into the test section of the ballistic range at supersonic speeds. Direction-indicating color schlieren method (DInCS) was used to visualize the flow field. The stand-off distance of the detached shock waves and the shape were obtained as the function of Mach number. The functions were compared with the results obtained by wind tunnel experiments. Analyzed images provided the quantitative information on shock shapes. The results were as follows: (1) the stand-off distances of the detached shock waves have been shown as exponential functions of Mach number; (2) the shapes of the shock waves have been found as quadratic functions of Mach number. The differences in the functions between this paper and a wind tunnel test were shown.

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Visualization of developing high temperature supersonic impulse jet induced by blast wave simulator

Cited by 4 publications

References 13 publications

Modeling and Simulation of Back Blast Flow Field of a Recoilless Gun Launching in Finite Space

Modeling and Simulation of Back Blast Flow Field of a Recoilless Gun Launching in Finite Space

Dynamic PIV measurement of a high-speed flow issuing from vent-holes of a curtain-type airbag

Detached shock waves around cylinders flying at mach number ranging from 1 to 2

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