Experimental and Numerical Studies of Toroidal Ballute in Hypersonic Shock Tunnel

Pooja Chaubdar; AB Harichandan; Ashish Vashishtha; G Jagadeesh

Experimental and Numerical Studies of Toroidal Ballute in Hypersonic Shock Tunnel

Pooja Chaubdar, AB Harichandan, Ashish Vashishtha, G Jagadeesh

Department of Aerospace and Mechanical Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution

Abstract

The present study aims to characterize the unsteady flow field of re-entry vehicle and ballute system. The experimental and numerical flow field analysis of a hayabusa re-entry vehicle with trailing toroidal ballute have been performed at hypersonic Mach number 7.71. The experiments were performed at test-section of Hypersonic Shock Tunnel 2 modified to Ludwieg mode at LHSR, IISc, Bengaluru. The flow visualizations of unsteadiness are conducted using high-speed camera in Z-type Schlieren system at 20000 fps. The axisymmetric inviscid transient simulations were performed using rhoCentral-Foam solver at OpenFOAM platform to further understand the flow field. During the experiments, the downstream shock fluctuates in the range of 909-1052 Hz. The maximum amplitude of shock fluctuation is observed at x/D= 4.5, because of Edney Type IV shock-shock interaction.

Original language	English
Title of host publication	6th National Symposium on Shock Waves, Feb 26-28, 2020, Chennai, INDIA
Publication status	Published - 28 Feb 2020

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@inproceedings{fbc9781f745b448a8b3e4f6abf05dd31,

title = "Experimental and Numerical Studies of Toroidal Ballute in Hypersonic Shock Tunnel",

abstract = "The present study aims to characterize the unsteady flow field of re-entry vehicle and ballute system. The experimental and numerical flow field analysis of a hayabusa re-entry vehicle with trailing toroidal ballute have been performed at hypersonic Mach number 7.71. The experiments were performed at test-section of Hypersonic Shock Tunnel 2 modified to Ludwieg mode at LHSR, IISc, Bengaluru. The flow visualizations of unsteadiness are conducted using high-speed camera in Z-type Schlieren system at 20000 fps. The axisymmetric inviscid transient simulations were performed using rhoCentral-Foam solver at OpenFOAM platform to further understand the flow field. During the experiments, the downstream shock fluctuates in the range of 909-1052 Hz. The maximum amplitude of shock fluctuation is observed at x/D= 4.5, because of Edney Type IV shock-shock interaction.",

author = "Pooja Chaubdar and AB Harichandan and Ashish Vashishtha and G Jagadeesh",

year = "2020",

month = feb,

day = "28",

language = "English",

booktitle = "6th National Symposium on Shock Waves, Feb 26-28, 2020, Chennai, INDIA",

}

TY - GEN

T1 - Experimental and Numerical Studies of Toroidal Ballute in Hypersonic Shock Tunnel

AU - Chaubdar, Pooja

AU - Harichandan, AB

AU - Vashishtha, Ashish

AU - Jagadeesh, G

PY - 2020/2/28

Y1 - 2020/2/28

N2 - The present study aims to characterize the unsteady flow field of re-entry vehicle and ballute system. The experimental and numerical flow field analysis of a hayabusa re-entry vehicle with trailing toroidal ballute have been performed at hypersonic Mach number 7.71. The experiments were performed at test-section of Hypersonic Shock Tunnel 2 modified to Ludwieg mode at LHSR, IISc, Bengaluru. The flow visualizations of unsteadiness are conducted using high-speed camera in Z-type Schlieren system at 20000 fps. The axisymmetric inviscid transient simulations were performed using rhoCentral-Foam solver at OpenFOAM platform to further understand the flow field. During the experiments, the downstream shock fluctuates in the range of 909-1052 Hz. The maximum amplitude of shock fluctuation is observed at x/D= 4.5, because of Edney Type IV shock-shock interaction.

AB - The present study aims to characterize the unsteady flow field of re-entry vehicle and ballute system. The experimental and numerical flow field analysis of a hayabusa re-entry vehicle with trailing toroidal ballute have been performed at hypersonic Mach number 7.71. The experiments were performed at test-section of Hypersonic Shock Tunnel 2 modified to Ludwieg mode at LHSR, IISc, Bengaluru. The flow visualizations of unsteadiness are conducted using high-speed camera in Z-type Schlieren system at 20000 fps. The axisymmetric inviscid transient simulations were performed using rhoCentral-Foam solver at OpenFOAM platform to further understand the flow field. During the experiments, the downstream shock fluctuates in the range of 909-1052 Hz. The maximum amplitude of shock fluctuation is observed at x/D= 4.5, because of Edney Type IV shock-shock interaction.

M3 - Conference contribution

BT - 6th National Symposium on Shock Waves, Feb 26-28, 2020, Chennai, INDIA

ER -

Experimental and Numerical Studies of Toroidal Ballute in Hypersonic Shock Tunnel

Abstract

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