Analytical Method of Evaluating Nonuniformities in Shock Tube Flows: Theory and Development
TL;DR: In this article , a quasi-one-dimensional analytical methodology for predicting the nonuniformities in the post-shock test gas based exclusively on the experimentally measured history of shock speed down the tube is presented.
read more
Abstract: Shock tube experiments are a cornerstone of investigations into the hypersonic flight environment. However, the actual flow through the basic shock tube has not been well characterized in the literature, and nonuniformities arising in the test gases are not well understood. This work produces a quasi-one-dimensional analytical methodology for predicting the nonuniformities in the postshock test gas based exclusively on the experimentally measured history of shock speed down the tube. Wave effects extracted from shock speed variations are shown to provide all information necessary in order to reconstruct the test slug from any particular experiment. Accurate representation of flow dynamics is initially checked against argon test cases following accelerating and decelerating shock trajectories, each with a tube-end Mach number of 6.5 and a fill pressure of 66.66 Pa in a tube of 100 mm diameter. Agreement between the method and results from a viscous, axisymmetric Navier–Stokes solution is found to be within 1% in pressure and temperature.
read more
Chat with Paper
AI Agents for this Paper
Find similar papers on Google Scholar, PubMed and Arxiv
Write a critical review of this paper
Analyze citations of this paper to find unaddressed research gaps
Citations
The influence of shock speed variation on radiation and thermochemistry experiments in shock tubes
TL;DR: In this paper , a series of experiments were conducted to confirm the importance of the shock deceleration effect on aerodynamic modeling of atmospheric entry vehicles using optical measurements of the test slug.
20
Spatial Transformations for Reacting Gas Shock Tube Experiments
TL;DR: In this article , the authors developed a method to approximately transform the post-shock distance for normal and blunt body shocks to a shock tube flow using a Mirels analysis, which is then applied to blunt body simulations of NASA EAST data for air and Titan tests.
6
Self-ignition and flow characteristics of pressurized hydrogen in Y-shaped tubes
Xuhai Pan,Yunyu Li,Yiming Jiang,Bahman Amini Horri,Tao Zhang,Zhilei Wang,Qingyuan Wang,Juncheng Jiang,Sanming Wang +8 more
TL;DR: In this paper , the authors investigated the propagation of shock waves and flame induced by a sudden pressure release of hydrogen in various Y-shaped tubes, and the impact of the initial burst pressure, downstream tube length, and bifurcation angle (60°, 120°) was analyzed by recording the pressure signals, photoelectric curves and jet fire evolution.
4
Analysis of Shock Deceleration Effects in the NASA Electric Arc Shock Tube
TL;DR: In this article , a recently developed numerical methodology (LASTA) is applied to these results from the literature, using the experimental shock speed profile as an input, trends in postshock electron density are computed.
4
Examination of Mars2020 shock-layer conditions via infrared emission spectroscopy of CO2
Augustin C. Tibère-Inglesse,Brett A. Cruden,Christopher Jelloian,R. Mitchell Spearrin +3 more
- 19 Jan 2023
TL;DR: In this article , a new test series was performed in the Electric Arc Shock Tube (EAST) facility, with the aim of reproducing flight conditions encountered during the Mars2020 mission entry into Mars atmosphere.
3
References
Test time in low pressure shock tubes
TL;DR: In this paper, the reduction of test time in low pressure shock tubes, due to a laminar wall boundary layer, has been analytically investigated, and it was found that β is considerably larger than the estimates made by Roshko and Hooker except for very strong shocks.
352
Shock Tube Test Time Limitation Due to Turbulent-Wall Boundary Layer
TL;DR: In this article, the authors investigated the test time limitation due to the premature arrival of the contact surface of the boundary layer and compared the results with those for wholly laminar-wall boundary layers, and found that, for a given shock Mach number, the maximum possible test time (in a long shock tube) varies as d 6/4p co1/4 and d2p CD for both air and argon.
252
About the formulation, verification and validation of the hypersonic flow solver Eilmer
Rowan J. Gollan,Peter A. Jacobs +1 more
TL;DR: The formulation of the gas dynamics and high-temperature thermochemical modules of the Eilmer code, an open-source Navier-Stokes solver for transient compressible flow in two and three dimensions, is described and verification and validation cases are described in full detail.
149
Influence of diaphragm opening time on shock-tube flows
TL;DR: In this paper, the authors used the equilibrium Hugoniotiot for the driven gas, both for the usual model of shock tube flow and for a suggested model based on a finite rupture time for the diaphragm.
139
Flow Nonuniformity in Shock Tubes Operating at Maximum Test Times
TL;DR: In this article, the authors investigated the nonuniformity of the flow in the limit where the shock and contact surface have reached their maximum separation and found that all fluid properties increase with the ratio of specific heat to specific Mach number.
136