Experimental investigation of interactions between turbulent cylinder wake and spherical shock wave

Aruga, Kenta; Inokuma, Kento; Watanabe, Tomoaki; Nagata, Koji; Sakai, Yasuhiko

doi:10.1063/1.5128267

Cited by 7 publications

(1 citation statement)

References 46 publications

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“…The influence of compressibility on vorticity fluctuation after the interaction was also examined. In attempting to evaluate the turbulent parameters across the interaction, the interaction of turbulent cylindrical wake and spherical shock wave was investigated experimentally by Aruga et al (2020). The effects on the integral length scale of freestream turbulence on junction flow behavior have been demonstrated and the data of such a kind of study show the dependency of shock strength on the amplification of the turbulence (Lange and Lynch, 2020).…”

Section: Introductionmentioning

confidence: 99%

Numerical study of freestream turbulence effects on the nose cones in supersonic flow

Velmani

Suresh

2022

AEAT

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Purpose This paper aims to numerically investigate the influence of shock wave and freestream turbulence interaction on the parabolic and spherically blunted nose cones at supersonic speed. Design/methodology/approach Using density-based solver, the three-dimensional steady-state simulation is carried out. The working fluid is calorically perfect that obeys ideal gas law and the no-slip boundary conditionis given to the surface of the nose cone. Pressure far-field boundary condition is imposed at the boundary of the computational domain by giving freestream Mach number, freestream static pressure and temperature. Findings The growth rate of the boundary layer is faster on the spherically blunted nose cone, hence, the overall drag force is higher than the parabolic nose cone. Temperature at the edge of the boundary layer is increased due to the early ampli-fication of instabilities by the upstream disturbance. In this sense, the effects of freestream turbulence depend on its level, freestream conditions, strength and type of shock wave and zone of influence. Research limitations/implications Simulations are carried out for the flow Mach number 2.0 at zero angles of attack for the freestream conditions of the flow at an altitude of 10,000 m. Practical implications The phenomenon of shock wave–turbulence interaction occurs in flow regimes from transonic to hypersonic speeds and finds a wide range of applications, especially in the design of aircraft and missiles configurations. Originality/value The phenomenon of compression wave and freestream turbulence interaction around the commonly used nose cones in the case of aircraft, missiles, etc., is investigated. The performance characteristics such as aerodynamic drag, boundary layer dynamics and the nature of flow around the different nose cones at zero angle of attack are illustrated.

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Section: Introductionmentioning

confidence: 99%

Numerical study of freestream turbulence effects on the nose cones in supersonic flow

Velmani

Suresh

2022

AEAT

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Diaphragmless shock tube with multiple air-operated valves

Inokuma

Maeda²,

Watanabe³

et al. 2022

Exp Fluids

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Statistical analysis of deformation of a shock wave propagating in a local turbulent region

2020

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Direct numerical simulation is performed for analyzing the interaction between a normal shock wave and turbulence. The shock wave is initially located in a quiescent fluid and propagates into a local turbulent region. This flow setup allows investigation of the initial transition and statistically steady stages of the interaction. Shock deformation is quantified using the local shock wave position. The root-mean-square (rms) fluctuation in the shock wave position increases during the initial stage of the interaction, for which the time interval divided by the integral time scale increases with Mt2/(Ms2−1), where Mt is a turbulent Mach number and Ms is a shock Mach number. In late time, the rms fluctuation in the shock wave position hardly depends on the propagation time and follows a power law, [Mt2/(Ms2−1)]0.46, whose exponent is similar to the power law exponent of the rms pressure-jump fluctuation reported in experimental studies. Fluctuations in the shock wave position have a Gaussian probability density function. The spectral analysis confirms that the length scale that characterizes shock wave deformation is the integral length scale of turbulence. The fluctuating shock wave position is correlated with dilatation of the shock wave, where the correlation coefficient increases with Mt/(Ms − 1). In addition, the shock wave that deforms backward tends to be stronger than average and vice versa. Mean pressure jumps across the shock wave are different between areas with forward and backward deformations. This difference increases with the rms fluctuation in the shock wave position and is well-represented as a function of Mt2/(Ms2−1).

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Experimental investigation of interactions between turbulent cylinder wake and spherical shock wave

Cited by 7 publications

References 46 publications

Numerical study of freestream turbulence effects on the nose cones in supersonic flow

Numerical study of freestream turbulence effects on the nose cones in supersonic flow

Diaphragmless shock tube with multiple air-operated valves

Statistical analysis of deformation of a shock wave propagating in a local turbulent region

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