Showing papers in "Shock Waves in 2011"

Experimental research on the rotating detonation in gaseous fuels–oxygen mixtures

Abstract: An experimental study on rotating detonation is presented in this paper. The study was focused on the possibility of using rotating detonation in a rocket engine. The research was divided into two parts: the first part was devoted to obtaining the initiation of rotating detonation in fuel–oxygen mixture; the second was aimed at determination of the range of propagation stability as a function of chamber pressure, composition, and geometry. Additionally, thrust and specific impulse were determined in the latter stage. In the paper, only rich mixture is described, because using such a composition in rocket combustion chambers maximizes the specific impulse and thrust. In the experiments, two kinds of geometry were examined: cylindrical and cylindrical-conic, the latter can be simulated by a simple aerospike nozzle. Methane, ethane, and propane were used as fuel. The pressure–time courses in the manifolds and in the chamber are presented. The thrust–time profile and detonation velocity calculated from measured pressure peaks are shown. To confirm the performance of a rocket engine with rotating detonation as a high energy gas generator, a model of a simple engine was designed, built, and tested. In the tests, the model of the engine was connected to the dump tank. This solution enables different environmental conditions from a range of flight from 16 km altitude to sea level to be simulated. The obtained specific impulse for pressure in the chamber of max. 1.2 bar and a small nozzle expansion ratio of about 3.5 was close to 1,500 m/s.

Prediction of clearing effects in far-field blast loading of finite targets

Abstract: It is well known that when a blast wave strikes the face of a target, the duration of the loading, and hence the total impulse imparted to the target may be influenced by the propagation of a rarefaction, or “clearing” wave along the loaded face of the target adjacent to free edges. Simple methods of predicting the effect of clearing on reducing the blast loading impulse have been available for many years, but recent studies have questioned the accuracy and physical basis of these approaches. Consequently, several authors have used numerical modelling and/or experimental techniques to determine empirical predictive methods for the clearing effect. In fact, the problem had been addressed more than 50 years ago in a study which appears to have been since overlooked by the blast research fraternity. This article presents the results of that earlier study, and provides experimental validation. The analytical predictions are very simple to determine, and are shown to be in excellent agreement with experimental results.

Mesoscale analysis of volumetric and surface dissipation in granular explosive induced by uniaxial deformation waves

Abstract: A Lagrangian finite and discrete element technique, combined with a finite deformation, thermo-elastic-viscoplastic, and stick-slip friction theory, is used to computationally examine volumetric and surface dissipation within the meso-structure of granular explosive (HMX, C4H8N8O8) induced by uniaxial deformation waves. Emphasis is placed on characterizing the fraction of mass heated to elevated temperature (referred to as hot-spot mass fraction) by quasi-steady waves due to plastic and friction work and its dependence on wave strength. Predictions for a large, randomly packed ensemble of HMX particles having a solid volume fraction of 0.85 and a mean diameter of 60 μm show that plastic work principally affects the average temperature, whereas friction work affects the high frequency, high-temperature fluctuations that are likely responsible for combustion initiation. Cumulative distributions for hot-spot mass within the wave indicate that most mass (~99.9%) is heated to approximately 330, 400, and 500 K by plastic work for impact speeds of 50, 250, and 500 m/s, respectively, with a small fraction (~0.001%) heated to 600, 1,100, and 1,400 K by friction work. The hot-spot mass fraction induced by plastic work is well described by a Gamma distribution, though significant departures occur in the high-temperature end of the distribution due to friction work, even at higher impact speeds. Consequently, it is not possible to describe hot-spot mass fraction curves by a single classical distribution function. Implications of the predicted hot-spot mass fraction on granular HMX combustion are discussed.

Free-piston driver optimisation for simulation of high Mach number scramjet flow conditions

Abstract: The University of Queensland (UQ) is currently developing high Mach number, high total pressure scramjet flow conditions in its X2 and X3 expansion tube facilities. These conditions involve shock-processing a high-density air test gas followed by its unsteady expansion into a low-pressure acceleration tube. This relatively slow shock-processing requires the driver to supply high pressure gas for a significantly greater duration than normally required for superorbital flow conditions. One technique to extend the duration is to operate a tuned free-piston driver. For X2, this involves the use of a very light piston at high speeds so that, following diaphragm rupture, the piston displacement substitutes for vented driver gas, thus maintaining driver pressure much longer. However, this presents challenges in terms of higher piston loading and also safely stopping the piston. This article discusses the tuned driver concept, the design of a very lightweight but highly stressed piston, and details the successful development of a new set of tuned free-piston driver conditions for X2.

Effects of steady flow heating by arc discharge upstream of non-slender bodies

Abstract: The influence of steady energy addition into the flow by a low-voltage DC-arc discharge located upstream of conically nosed and spherically blunted bodies was investigated experimentally in the Ludwieg-Tube Facility at Mach 5. The results include drag force measurements and shadowgraph flow visualizations. The flow-field structure, arising due to the bow-shock/heated-wake interaction, as well as the bow-shock intensity and heating power effects on the drag reduction is analyzed in this paper. The results demonstrate the existence of an optimum heating rate, providing a maximum effectiveness of energy addition and showing distinct drag reductions up to 70% dependent on test conditions and model geometries.

Hot spot formation from shock reflections

Abstract: Heterogeneities sensitize an explosive to shock initiation. This is due to hot-spot formation and the sensitivity of chemical reaction rates to temperature. Here, we describe a numerical experiment aimed at elucidating a mechanism for hot-spot formation that occurs when a shock wave passes over a high-density impurity. The simulation performed is motivated by a physical experiment in which glass beads are added to liquid nitromethane. The impedance mismatch between the beads and the nitromethane results in shock reflections. These, in turn, give rise to transverse waves along the lead shock front. Hot spots arise on local portions of the lead front with a higher shock strength, rather than on the reflected shocks behind the beads. Moreover, the interactions generated by reflected waves from neighboring beads can significantly increase the peak hot-spot temperature when the beads are suitably spaced.

Growth rate predictions of single- and multi-mode Richtmyer–Meshkov instability with reshock

Abstract: The single- and multi-mode Richtmyer–Meshkov instabilities (RMI) with reshock are numerically analyzed in two- and three-dimensional domains. Four different types of air/SF6 interface shapes are investigated in a shock tube configuration, and the predicted post-reshock growth rates are compared with available empirical models of Mikaelian’s (Physica D 36(3):343–347, 1989) and Charakhch’an’s (J Appl Mech Tech Phys 41(1):23–31, 2000). The simulation of 3D multi-mode RMI shows good agreement with a past experimental study, but other interface types (2D single-mode, 2D multi-mode and 3D single-mode) result in different growth rates after reshock. Parametric studies are therefore performed to investigate the sensitivities of the post-reshock growth rates to model the empirical parameters. For single-mode RMI configurations, the interface shape is found to be only a weak function of the post-reshock growth rate, as also predicted by previous reshock models. The post-reshock growth rate shows a linear correlation to the velocity jump due to reshock; however, it is only about a half of the prediction of Charakhch’an’s model even though the growth before reshock compares well with pre-reshock models. The 3D single-mode post-reshock RMI growth rate is nearly 1.6 times larger than the 2D single-mode RMI. The parametric studies of multi-mode RMI show two distinctly different growth rates depending on the mixing conditions at reshock. If the interface remains sharp at the time of reshock, the post-reshock growth rate is as large as the single-mode cases. However, if the interface is mixed due to non-linear interactions of bubbles and spikes, the growth rates becomes slow and independent of the interface shapes. Overall, this study provides new insights into the flow features of reshocked RMI for different initial perturbation types.

Comparison of different models for non-equilibrium CO2 flows in a shock layer near a blunt body

Abstract: The paper presents results of a numerical simulation of a supersonic two-dimensional (2D) viscous flow containing CO2 molecules near a spacecraft entering the Mars atmosphere. The gas–dynamic equations in the shock layer are coupled to the equations of non-equilibrium vibrational and chemical kinetics in the five-component mixture CO2/CO/O2/C/O. Transport and relaxation processes in the flow are studied on the basis of the rigorous kinetic theory methods; the developed transport algorithms are incorporated in the numerical scheme. The influence of the vibrational excitation of CO2 and chemical reactions on the gas flow parameters and heat transfer is analyzed. The obtained results are compared with those found using two simplified models based on the two-temperature and one-temperature vibrational distributions in CO2. The accuracy of the simplified models and the limits of their validity within the shock layer are evaluated. The effect of bulk viscosity in a flow near a re-entry body is discussed. The role of different diffusion processes, chemical reactions, and surface catalytic properties in a flow of the considered mixture in the shock layer is estimated.

Application of Particle Image Velocimetry and the Background Oriented Schlieren Technique in the High-Enthalpy Shock Tunnel Göttingen

Abstract: The applicability of the particle image velocimetry (PIV) and the background-oriented schlieren (BOS) techniques in the high-enthalpy shock tunnel Gottingen of the German Aerospace Center, DLR is demonstrated As a part of this feasibility study two different experiments are performed The velocity field past a wedge in a Mach 6 flow at a total specific enthalpy of 15 MJ/kg is determined by means of PIV and the results are compared to numerical predictions The BOS technique is applied to investigate the density field in the shock layer of a sphere at 12 and 22 MJ/kg total specific enthalpies Using a ray tracer method, the BOS results are compared to the data obtained by corresponding numerical computations

Computational and experimental study of supersonic flow over axisymmetric cavities

Abstract: Laminar and turbulent computations are presented for annular rectangular-section cavities, on a body of revolution, in a Mach 2.2 flow. Unsteady ‘open cavity flows’ result for all laminar computations for all cavity length-to-depth ratios, L/D (1.33, 10.33, 11.33 and 12.33). The turbulent computations produce ‘closed cavity flows’ for L/D of 11.33 and 12.33. Surface pressure fluctuations at the front corner of the L/D = 1.33 cavity are periodic in some cases depending on the cavity length and depth, the boundary layer at the cavity front lip and the cavity scale. The turbulent computations are supported by experimental schlieren images, obtained using a spark light source, and time-averaged surface pressure data.

Pulsating stochastic flows accompanying microwave filament/supersonic shock layer interaction

Abstract: The details of pulsating stochastic flows accompanying the interaction of a microwave filament (regarded as a heated rarefied channel) and an aerodynamic body in supersonic flow are examined numerically using the Euler equations. Symmetrical and asymmetrical filament locations relative to the aerodynamic body are considered. The flowfields are characterized by large scale pulsations and small scale stochastic fluctuations. The mechanisms of the formation of these flow structures are discussed. Two qualitatively different kinds of flowfields are observed depending on the magnitude of the filament radius, with domination of the pulsations of flow parameters or stochastic phenomena. Flow instabilities inherent to the problems under interest are described. The problems are considered in both plane and cylindrical configurations for a wide class of filament characteristics and freestream Mach numbers equal to 1.89 and 3.

Numerical study of the detonation structure in rich H2−NO2/N2O4 and very lean H2−N2O mixtures

Abstract: In some mixtures and under certain conditions, detonation soot records show substructures. In nitromethane and nitrogen tetroxide mixtures, particular cellular structures can be observed. This kind of structures has been reported as the so-called double cellular structure. One- and two-dimensional simulations of detonation have shown that the double cellular structure is related to a non-monotonous energy release. Two-step energy release is also observed in rich H2−NO2/N2O4 and in very lean H2−N2O mixtures. The present study aims at the investigation of the effect of the energy release profile on the detonation structure in these two mixtures through numerical simulations. The origin of the non-monotonous energy release is explained in both mixtures using one-dimensional simulations with detailed chemistry. Reduced kinetic schemes are obtained and used to perform two-dimensional simulations. It is shown that in rich H2−NO2/N2O4 mixtures, the double cellular structure appears, whereas in very lean H2−N2O mixtures, classical substructures are observed. Both behaviours are explained based on ZND calculations and previous stability results. Phenomenological considerations led the authors to link the formation of the double cellular structure with the appearance of a large scale instability mode (a super cellular structure).

Wave propagation in gaseous small-scale channel flows

Abstract: The propagation and attenuation of an initial shock wave through a mm-scale channel of circular cross-section over lengths up to 2,000 diameters is examined as a model problem for the scaling of viscous effects in compressible flows. Experimental wave velocity measurements and pressure profiles are compared with existing data and theoretical predictions for shock attenuation at large scales and low pressures. Significantly more attenuation is observed than predicted based on streamtube divergence. Simulations of the experiment show that viscous effects need to be included, and the boundary layer behavior is important. A numerical model including boundary layer and channel entrance effects reproduces the wave front velocity measurements, provided a boundary layer transition model is included. A significant late-time pressure rise is observed in experiments and in the simulations.

Interaction of heated filaments with a blunt cylinder in supersonic flow

Abstract: A computational study is performed to examine the influence of pulsed energy deposition on a cylinder in supersonic flow. A code is written to solve the compressible Navier–Stokes equations. The energy deposition is modeled as a high temperature, low density filament introduced at the inflow boundary, and the frequency of energy deposition pulses is varied. It is shown that the energy deposition reduces both the average drag and the average heat transfer to the front face of the cylinder. The effectiveness of drag reduction is shown to be inversely proportional to the energy deposition pulsation period. The efficiency of drag reduction is shown to be approximately 100. The average heat transfer to the face is reduced from the steady state, with a maximum reduction of 30%.

Simulation of converging cylindrical GPa-range shock waves generated by wire array underwater electrical explosions

Abstract: Results of one-dimensional numerical simulations of the parameters of the converging strong shock wave generated by electrical underwater explosions of a cylindrical wire array with different array radii and different deposited energies are presented. It was shown that for each wire array radius there exists an optimal duration of the energy deposition into the exploding array, which allows one to maximize the shock wave pressure and temperature in the vicinity of the implosion axis. The simulation results agree well with the 130-GPa pressure in the vicinity of the implosion axis that was recently obtained, which strongly indicates the azimuthal symmetry of the converging shock wave at these extreme conditions. Also, simulations showed that using a pulsed power generator with a stored energy of ~200 kJ, the pressure and temperature at the shock wave front reaches ~220 GPa and 1.7 eV at 0.1 mm from the axis of implosion in the case of a 2.5 mm radius wire array explosion. It was found that, in spite of the complicated equation of state of water, the maximum pressure at the shock wave front at radius r can be estimated as P ≈ (P*(r*/r)α, where P* is the known value of pressure at the shock wave front at radius r* ≥ r and α is a parameter that equals 0.62±0.02. A rough estimate of the implosion parameters of the hydrogen target after the interaction with the converging strong shock wave is presented as well.

Diaphragmless shock wave generators for industrial applications of shock waves

Abstract: The prime focus of this study is to design a 50 mm internal diameter diaphragmless shock tube that can be used in an industrial facility for repeated loading of shock waves. The instantaneous rise in pressure and temperature of a medium can be used in a variety of industrial applications. We designed, fabricated and tested three different shock wave generators of which one system employs a highly elastic rubber membrane and the other systems use a fast acting pneumatic valve instead of conventional metal diaphragms. The valve opening speed is obtained with the help of a high speed camera. For shock generation systems with a pneumatic cylinder, it ranges from 0.325 to 1.15 m/s while it is around 8.3 m/s for the rubber membrane. Experiments are conducted using the three diaphragmless systems and the results obtained are analyzed carefully to obtain a relation between the opening speed of the valve and the amount of gas that is actually utilized in the generation of the shock wave for each system. The rubber membrane is not suitable for industrial applications because it needs to be replaced regularly and cannot withstand high driver pressures. The maximum shock Mach number obtained using the new diaphragmless system that uses the pneumatic valve is 2.125 ± 0.2%. This system shows much promise for automation in an industrial environment.

The hypersonic Mach number independence principle in the case of viscous flow

Abstract: The hypersonic Mach number independence principle of Oswatitsch is important for hypersonic vehicle design. It explains why, above a certain flight Mach number (M∞ ≈ 4−6, depending on the body shape), some aerodynamic properties become independent of the flight Mach number. For ground test facilities this means that it is sufficient for the Mach number in the test section to be high enough, that Mach number independence exists. However, the principle was derived for calorically perfect gas and inviscid flow only. In this paper a theoretical study for blunt bodies in the case of viscous flow is presented. We provide numerical results which give insight into how attached viscous flow behaves at high Mach numbers. The flow past an axisymmetric configuration is analysed by applying a coupled Euler/second-order boundary-layer method. Wall boundaries are treated by assuming an adiabatic or radiation-adiabatic wall for laminar flow. Calorically perfect or equilibrium air is accounted for. Lift, drag, and moment coefficients, and lift-to-drag ratios are given for several combinations of flight Mach number and altitude, i.e. Reynolds number. For blunt bodies considered here, which are pressure dominated, Mach number independence occurs for the adiabatic wall, but not for the radiation-adiabatic wall assumption.

Blast wave attenuation through a composite of varying layer distribution

Abstract: The interaction of a blast wave with a multi-layered material is investigated for the purpose of blast wave attenuation. For a fixed total mass and thickness of material, the effect of layering of the materials in the system on shock wave transmission is considered based on theoretical and experimental results. The system of materials is a discrete set of steel and low density foam plates of varying thicknesses. A wave tracking algorithm is employed to predict the behavior of the system with respect to simple wave interactions assuming elastic materials. The theoretical results are used to identify the change in wave dynamics caused by altering the distribution of the material layers. It has been shown that the time scale corresponding to stress equilibration across the high-low impedance material interfaces in the system dominates the behavior of the system and that the stress transfer is limited by the low impedance material.

Effect of wall heat transfer on shock-tube test temperature at long times

Abstract: When performing chemical kinetics experiments behind reflected shock waves at conditions of lower temperature ( 8cm). Smaller diameters on the order of 3 cm or less can experience significant temperature loss near the reflected-shock region. Although the area-averaged gas temperature decreases due to the heat loss, the main core region remains spatially uniform so that the zone of temperature change is limited to only the thermal layer adjacent to the walls. Although the heat conduction model assumes the gas and wall to behave as solid bodies, resulting in a core gas temperature that remains constant at the initial temperature, a two-zone gas model that accounts for density loss from the core to the colder thermal layer indicates that the core temperature and gas pressure both decrease slightly with time. A full CFD solution of the shock-tube flow field and heat transfer at long test times was also performed for one typical condition (800 K, 1 atm, Ar), the results of which indicate that the simpler analytical conduction model is realistic but somewhat conservative in that it over predicts the mean temperature loss by a few Kelvins. This paper presents the first comprehensive study on the effects of long test times on the average test gas temperature behind the reflected shock wave for conditions representative of chemical kinetics experiments.

Shock wave structure for a fully ionized plasma

Abstract: We study planar shock wave structure in a two-temperature model of a fully ionized plasma that includes electron heat conduction and energy exchange between electrons and ions. For steady flow in a reference frame moving with the shock, the model reduces to an autonomous system of ordinary differential equations which can be numerically integrated. A phase space analysis of the differential equations provides an additional insight into the structure of the solutions. For example, below a threshold Mach number, the model produces continuous solutions, while above another threshold Mach number, the solutions contain embedded hydrodynamic shocks. Between the threshold values, the appearance of embedded shocks depends on the electron diffusivity and the electron–ion coupling term. We also find that the ion temperature may achieve a maximum value between the upstream and downstream states and away from the embedded shock. We summarize the methodology for solving for two-temperature shocks and show results for several values of shock strength and plasma parameters in order to quantify the shock structure and explore the range of possible solutions. Such solutions may be used to verify hydrodynamic codes that use similar plasma physics models.

A rapid opening sleeve valve for a diaphragmless shock tube

Abstract: This paper describes a novel pneumatically operated diaphragmless shock tube valve that is capable of generating well-formed shock waves within a driven tube which has a length to diameter ratio of 122. Its development was motivated by the requirement for an automated shock tube—an application for which the conventional bursting diaphragm method is not suited. The valve operates reliably, without any need for adjustment to its setup, over a wide range of driver pressures. Shock waves of up to Mach 2.4 have been generated in test gas at atmospheric pressure. A model for assessing the performance of the valve was developed and calibrated with experimental data. It indicated that opening times in the region of 0.5 ms were attained. By comparison, the opening time of a burst diaphragm is approximately 0.2–0.3 ms. Features of the valve include a streamlined flow path, which helps optimise the efficiency of the shock tube, automated operation and a test turn around time of the order of a few minutes.

Experimental investigation of a twice-shocked spherical gas inhomogeneity with particle image velocimetry

Abstract: Results are presented from an experimental investigation into the interaction of a planar shock wave with a vortex ring. A free-falling spherical soap bubble is traversed by the incident shock wave and develops into a vortex ring as a result of baroclinically deposited vorticity (\({ abla\rho\times abla p eq 0}\)). The vortex ring translates with a velocity relative to the particle velocity behind the shock wave due to circulation. After the shock wave reflects from the tube end wall, it traverses the vortex ring (this process is called “reshock”) and deposits additional vorticity. Planar Mie scattering is used to visualize the atomized soap film at high frame rates (up to 10,000 fps). Particle image velocimetry (PIV) was performed for an argon bubble in nitrogen accelerated by a M = 1.35 shock wave. Circulation was determined from the PIV velocity field and found to agree well with Kelvin’s vortex ring model.

Shock wave reflection off coupled surfaces

Abstract: It has been shown that when a plane shock wave is reflected off a surface consisting of a 75-mm radius circular arc followed by a plane section inclined at 45°, it takes some time for the interaction to reach a pseudosteady reflection configuration. The current study extends this work at a constant Mach number of 1.346, with three compound walls, consisting of leading circular sections of 30, 50 and 75 mm radius, joined to a plane wall section. Testing was done at various wall angles for each of the test pieces. The reflected wave angle was measured and was found to increase along the plane wall section until it reached an asymptotic value, at which time pseudosteady flow was established. The asymptotic values are consistent with reflection off plane wedges and are independent of the leading radius. For lower wall angles which lead to Mach reflection the length required to reach pseudosteady flow increases as the wall angle increases to the pseudosteady transition angle. The reverse occurs when the final pseudosteady reflection is regular, in that as the wall angle increases the distance travelled to reach pseudosteady flow conditions decreases. Additional tests were conducted on a specimen consisting of a plane section at 60° wall angle with 30-mm radius circular arc sections at either end. It is demonstrated how the information from the two slope changes influences the shape of the reflected shock. The trajectories of two perturbations on the reflected shock arising from the joints between the circular sections and the plane wall show that the reflected wave remains linear between these two points, as it received no knowledge from either circular section until the perturbations from the upper and lower joints cross.

Investigation of the unsteadiness of a shock-reflection interaction with time-resolved particle image velocimetry

Abstract: The spatio-temporal dynamics of an impinging shock/boundary layer interaction at Mach 2 and under incipient separation conditions, has been investigated experimentally by means of high-speed particle image velocimetry (PIV). The available PIV acquisition rate of up to 20 kHz permits a time-resolved characterization of the interaction. The dynamics of different flow regions—notably the separation region and the reflected shock—were quantified by means of temporal auto-correlation fields and pseudo-spectral analysis. The PIV data further enable to investigate the relationship between spatially extended flow features, such as shock position and bubble size, as well as the influence of the upstream boundary layer. The results confirm earlier studies that there is an important upstream effect on the present incipient interaction.

Numerical simulation of Mach reflection in steady flows

Abstract: The structure obtained when two shocks intersect is known to be highly sensitive to various parameters. In the so-called dual solution domain, both regular and Mach reflection patterns are possible, resulting in hysteresis. The phenomenon is important in inlets because of the substantial difference in entropy rise associated with the two manifestations, and the possibility of unstart with Mach reflection. The effect of various numerical and physical parameters on hysteresis are investigated with two-dimensional simulations. The effect of spanwise relief on a three-dimensional situation is also elucidated. It is confirmed that Mach-stem heights determined from inviscid computations are captured relatively accurately by comparison with experimental data and earlier Euler solutions reported in the literature. Near bifurcation points, however, the solution is highly sensitive to the scheme, and the van Leer and Roe schemes can yield converged solutions with different reflection configurations. Viscous terms and downstream conditions are observed to have relatively minor impact on the solution. The three-dimensional simulations reveal that beyond the spanwise limit of the compression surface, the overall shock-structure remains similar in form but the strengths of various shocks are rapidly muted by the expansion from the side surface. Additionally, the flow downstream of the shock that once formed the Mach reflection rapidly becomes supersonic. The Mach-stem height on the symmetry plane and its variation with spanwise position shows reasonable agreement with the experimental data of other investigators.

Near-wall imaging using toluene-based planar laser-induced fluorescence in shock tube flow

Abstract: A quantitative thermometry technique, based on planar laser-induced fluorescence (PLIF), was applied to image temperature fields immediately next to walls in shock tube flows. Two types of near-wall flows were considered: the side wall thermal boundary layer behind an incident shock wave, and the end wall thermal layer behind a reflected shock wave. These thin layers are imaged with high spatial resolution (15μm/pixel) in conjunction with fused silica walls and near-UV bandpass filters to accurately measure fluorescence signal levels with minimal interferences from scatter and reflection at the wall surface. Nitrogen, hydrogen or argon gas were premixed with 1–12% toluene, the LIF tracer, and tested under various shock flow conditions. The measured pressures and temperatures ranged between 0.01 and 0.8 bar and 293 and 600 K, respectively. Temperature field measurements were found to be in good agreement with theoretical values calculated using 2-D laminar boundary layer and 1-D heat diffusion equations, respectively. In addition, PLIF images were taken at various time delays behind incident and reflected shock waves to observe the development of the side wall and end wall layers, respectively. The demonstrated diagnostic strategy can be used to accurately measure temperature to about 60 μm from the wall.

Simplified modeling of blast waves from metalized heterogeneous explosives

Abstract: The detonation of a metalized explosive generates a complex multiphase flow field. Modeling the subsequent propagation of the blast front requires a detailed knowledge of the metal particle dynamics and reaction rate. Given the uncertainties in modeling these phenomena, a much simpler, 1D compressible flow model is used to illustrate the general effects of secondary energy release due to particle reaction on the blast front properties. If the total energy release is held constant, the blast pressure and impulse are primarily dependent on the following parameters: the proportion of secondary energy released due to afterburning, the rate of energy release, the location the secondary energy release begins, and the range over which it occurs. Releasing the total energy over a longer time period in general reduces the peak blast overpressure at a given distance. However, secondary energy release reduces the rate of decay of the shock pressure, increases the local gas temperature and hence increases the velocity of the secondary shock front. As a result, for certain values of the above parameters, the peak blast impulse may be increased by a factor of about two in a region near the charge. The largest augmentation to the near-field peak impulse results when the secondary energy is released immediately behind the shock front rather than uniformly within the combustion products.

Shock wave triple-point morphology

Abstract: The existence and characteristics of shock wave triple points are examined The analysis utilizes a single flow plane for the three shocks and is local to the triple point It applies when the flow is unsteady, three-dimensional, and the upstream flow is nonuniform Under more restrictive conditions, a relation is also derived for the ratio of the curvature of the Mach stem to that of the reflected shock For given values of the ratio of specific heats, γ, and the upstream Mach number, M1, a solution window is established A parametric set of solutions is generated within the window for γ = 1, 14, and 5/3 and for 16 values of M1 ranging from solution onset to M1 = 6A solution can be one of three types, these stem from the velocity tangency condition along the slip stream Topics are addressed such as solution multiplicity, shock wave and slip stream orientation, the nature of the reflected wave (weak, strong, inverted, normal), the nature of the Mach stem (weak, strong, normal), and differences due to changes in γ and M1

Numerical modelling of the entrainment of particles in inviscid supersonic flow

Abstract: The interaction between particles situated in close proximity and moving at supersonic speeds is investigated computationally. The simplest case of the motion of a single particle travelling behind a lead particle is used to elucidate the role of aerodynamic forces in the motion of a group of particles. The effect of the following parameters on the drag and lift forces acting on each of two particles of equal diameter in proximity is investigated: the free-stream Mach number, and the axial and lateral displacements of the trailing particle. The two-dimensional flow field is numerically simulated using an unsteady Euler CFD code to find the steady-state drag and lift coefficients for both particles. Three static zones of aerodynamic influence in the wake of the lead particle are identified, which are denoted as the entrainment, lateral attraction, and ejection zones. A non-dimensional representation of the zones of influence is given. It is shown that the dynamic entrainment of particles can occur even when the path of the trailing particle originates outside the entrainment and lateral attraction zones.

Freestream effects on base pressure development of an annular plug nozzle

Abstract: An experimental investigation has been carried out to study the effect of freestream flow and cowl-length variation on (i) upstream flow interference effects and (ii) the base wake-closure nozzle pressure ratio. It is observed that for supersonic freestream Mach numbers the nozzle exhaust seems to only slightly influence the upstream interference effects for M = 1.2 but shows significant influence for M = 1.6. Increasing the cowl-length further reduces the upstream flow interference effects significantly. Further, the reduced momentum thrust from the inner nozzle in the presence of freestream for similar nozzle pressure ratio (relative to static tests) delays the downstream movement of the system of shocks on the plug surface. In the case of the plug truncated at 40% length, this delays the onset of base-wake closure and hence, increases the base-wake closure nozzle pressure ratio with increasing freestream Mach number. Increasing the cowl-length also helps to increase the base pressure thrust contribution at all operating conditions.