On properties of the deterministic turbulence and reproducibility of its instantaneous and statistical characteristics

As known from previous studies, is a post-transitional flow that is turbulent the deterministic turbulence （DeTu） according to the generally accepted statistical characteristics but possesses, meanwhile, a significant degree of determinism, i.e., reproducibility of its instantaneous structure. It is found that the DeTu can occur in those cases when transition is caused by convective instabilities; in boundary layers, in particular. The present paper is devoted to a brief description of history of discovering the DeTu phenomenon, as well as to some recent advance in investigation of instantaneous and statistical properties of such turbulent boundary layer flows.

Cultural Heritage and Flood Need of Interdisciplinarity

This contribution discusses some results of the ongoing research focused on the protection of cultural heritage from flood danger. The research project Methodology of Protection and Rescue of Cultural Heritage against Flood takes place in the Czech Republic and is focused on specific regional problems that have been experienced during and after disastrous floods in past 15 years. However, the lessons learned have wider applicability to the issue of flood protection of cultural heritage. Here, we describe two case studies that represent important issues requiring a solution;addressing these issues was the main motivation for the whole project.

Stability of Subsonic Microjet Flows and Combustion

Results of experimental studies of round and plane propane microjet combustion in a transverse acoustic field at small Reynolds numbers are presented in this paper. Features of flame evolution under the given conditions are shown. Based on the new information obtained on free microjet evolution, new phenomena in flame evolution in a transverse acoustic field with round and plane propane microjet combustion are discovered and explained.

Theoretical and Engineering Approach to Human Power Ornithopter Design

The article considers the issues on preliminary calculation of human-powered ornithopter general performances. The model of “simple ornithopter” is introduced. Giving an example of simple ornithopter interaction with the environment, the formula of relation of ornithopter theoretically available propulsion to kinematic and physical parameters of its horizontal flight parameters is derived. The tasking is performed for the following stages of calculation and design of the human-powered ornithopter.

Experimental study of compressible boundary layer on a cone at angles of attack

Experimental study was conducted for boundarylayers on a sharp 5° half-angle cone of 400mm length at angles of attack. The model was tested in the T-326 hypersonic wind tunnel （ITAM） at freestream Mach number M = 5.95. Mean and fluctuation wall characteristics of the boundary layer are measured at 0°, 2°, 3° and 4° angles of attack for different stagnation pressures. Pulsation measurements are carried out by means of ALTP sensor. Pressure and temperature distributions along the model are obtained, and transition beginning and end locations have been found. Boundary layer stabilization with the increase of angle of attack and the decrease of stagnation pressure is observed. High frequency pulsations inherent to hypersonic boundary layer （second mode） have been detected.

Simulation of hydrocarbons pyrolysis in a fast-mixing reactor

Currently, thermal decomposition of hydrocarbons for the production of basic petrochemicals(ethylene, propylene) is carried out in steam-cracking processes. Aside from the conventional method, under consideration are alternative ways purposed for process intensification. In the context of these activities, the method of hightemperature pyrolysis of hydrocarbons in a heat-carrier flow is studied, which differs from previous ones and is based on the ability of an ultra-short time of feedstock/heat-carrier mixing. This enables to study the pyrolysis process at high temperature(up to 1500 K) at the reactor inlet. A set of model experiments is conducted on the lab scale facility. Liquefied petroleum gas(LPG) and naphtha are used as a feedstock. The detailed data are obtained on temperature and product distributions within a wide range of the residence time. A theoretical model based on the detailed kinetics of the process is developed, too. The effect of governing parameters on the pyrolysis process is analyzed by the results of the simulation and experiments. In particular, the optimal temperature is detected which corresponds to the maximum ethylene yield. Product yields in our experiments are compared with the similar ones in the conventional pyrolysis method. In both cases(LPG and naphtha), ethylene selectivity in the fast-mixing reactor is substantially higher than in current technology.

Pest Management in Museum Collections and Storage Areas （New ApproachmOnline Sensors for Pest Detection）

Common denominator and one of the goals in the ＂storage＂ of many, even different, commodities （agricultural, etc.） is their protection against invasion by biological pests; protection of objects of cultural heritage deposited in museums, galleries, archives and other institutions of a similar type is one of the specific case. The present article is an overview of basic （potential） biological pests of some ＂storage＂ commodities （with emphasis on the protection of objects of cultural heritage） as well as methods used for their detection. In the final section, a modular system of the ongoing assessment of the environmental characteristics of depositaries and exhibitions （including ＂biological＂） is briefly presented; its advantage is the possibility of on-line monitoring of the evaluated parameters （temperature, humidity, lighting, etc.） including the detection of presence of crawling and airborne insects.

Stability of Subsonic Jet Flows

An overview of recent experimental results on instability and dynamics of jets at low Reynolds numbers is given. Round and plane, macro and micro jets are under the consideration. Basic features of their evolution affected by initial conditions at the nuzzle outlet and environmental perturbations are demonstrated.

Linear Instability of the Supersonic Boundary Layer on a Compliant Surface

In the paper the influence of flexible covering properties on the linear development of disturbances in a supersonic boundary layer is investigated for Mach numbers M = 1.0, 2.0, 5.3, 6.0. As a model of a covering the porous plate closed by a flexible film is used. In the absence of gas in pores it is established that the flexible covering stabilizes boundary layer in the area of large Reynolds numbers and destabilizes it at small Reynolds numbers. Joint influence of the thickness and tension of a film leads to an appearance of additional unstable waves. For filled with gas pores the researches are conducted as taking into account losses of energy of disturbances in pores and in their absence. Calculations without power losses indicate possibility of existence of an absolute instability of the boundary layer on the flexible surface. The damping properties of a flexible covering connected with power losses in pores reduce their stabilizing role.

Simulation of Thermophysical Processes at Laser Welding of Alloys Containing Refractory Nanoparticles

Mathematical model is formulated for description of thermophysical processes at laser welding of metal plates for the case when modifying nanoparticles of refractory compounds (nanopowder inoculators – NPI) are introduced into the weld pool. Specially prepared nanoparticles of refractory compounds serve here as crystallization centers, i.e. in fact they are exogenous inoculants on which surface clusters are grouped. This can be used to control the melt crystallization process and formation of its structure, and, therefore, properties of the weld seam. As an example, calculation results of the butt welding of aluminum alloy and steel plates are presented. The results of calculation and experimental data comparison are shown.

Mechanical Characteristics of Chemically Degraded Surface Layers of Wood

The aim of this research was to find out whether the effect of chemical corrosion changes mechanical characteristics of surface layers of wooden construction elements. Degradation of the surface layers of wood was caused by chemical reactions of the basic substances of wood mass with compounds contained in antifire coatings. Fire retardants containing corrosive substances were often and repeatedly used in the Czech Republic on many wooden building constructions. This process of chemical corrosion is in practise called as ＂surface defibering of wood＂. This contribution presents standard and special experimental methods used for measuring the selected mechanical characteristics （compression strength, tension strength, bending strength, hardness and impact resistance） in the damaged surface layer of wooden construction elements. The material for experimental measuring was a construction element removed from a historical roof （ca 150 years old）. Mechanical characteristics of the surface layer of the defibered element were compared with the values measured in the deeper subsurface layer of non-damaged wood. The results of the experiments proved loss of cohesive strength and decrease of mechanical characteristics of wood only in a thin surface layer.

Experimental and numerical investigation of controlled disturbances development from two sources in supersonic boundary layer

The paper presents the experimental results and the results of direct numerical simulation of the development and interaction of two wave trains from two point sources of controlled disturbances in a supersonic boundary layer on a flat plate with an incident flow Mach number of 2.5.Sources were located parallel to the leading edge of the model.For the introduction of controlled disturbances into the boundary layer,the normal component of the mass flow rate was varied in the calculations.In the experiment,periodic glow discharges at a frequency of 20 kHz were used.In both cases,the disturbances sources worked synchronously.Mass flow rate pulsations were measured and recorded in sections,parallel to the leading edge of the model,near the maximum of disturbances along the boundary layer.In the experiment,a constanttemperature hot-wire anemometer was used.After performing a discrete Fourier transform,the spatial distributions of disturbances,the beta-spectra were determined,and the wave characteristics of the development of disturbances downstream were estimated.In addition,direct numerical simulation of the downstream development of disturbances from a single source was performed.The work presents a comparison of experimental and theoretical calculated data.The paper discusses the effects inherent in the interaction of unstable traveling controlled disturbances from two sources operating synchronously.

The Research of Laminar-Turbulent Transition in Hypersonic Three-Dimensional Boundary Layer

The results of experimental investigation of laminar-turbulent transition in three-dimensional flow under the high continuous pressure gradient including the flow with local boundary layer separation are presented. The experimental studies were performed within the Mach number range from 4 to 6 and Reynolds number 10-60×106 1/m, the angles of attack were 0° and 5°. The experiments were carried out on the three-dimensional convergent inlet model with and without sidewalls. The influence of artificial tubulator of boundary layer on transition and flow structure was studied. The conducted researches have shown that adverse pressure gradient increase hastens transition and leads to decrease of transition area length. If pressure gradient rises velocity profile fullness increases and profile transformation from laminar to turbulent occurs. As a result of it the decrease of separation area length occurs. The same effect was reached with Reynolds number increase. These results are compared with the data on two-dimensional model with longitudinal curvature.

On the calculation of the electron temperature flowfield in the DSMC studies of ionized re-entry flows

Currently available procedures of electron temperature calculations in studying ionized flows around reentry spacecraft by the direct simulation Monte Carlo(DSMC)method are analyzed.It is shown that the heat conduction of electrons is not taken into account in these procedures.The contributions of various effects to the electron energy balance are calculated by an example of the RAM-C II capsule,and a numerical solution of the electron energy conservation equation is obtained,which refines the electron temperature distribution used in the DSMC computations.A method of coupled calculation of the electron temperature within the framework of the continuum approach and modelling of ionized gas flow by the DSMC method is proposed.

Ignition of Hydrocarbon-Air Supersonic Flow by Volumetric Ionization

The paper describes the results of the electron-beam initiation of the combustion in the mixtures of hydrogen,natural gas or kerosene vapors with air.Electron beam characteristics were studied in closed volume with immobile gas.The researches included definition of an integrated current of an electronic beam,distribution of a current density and an estimation of average energy of electrons.Possibility of fuel mixtures ignition by means of this approach in the combustor at high velocity at the entrance was demonstrated.Experiments were carried out at Mach numbers of 4 and 5.Process of ignition and combustion under electron beam action was researched.It was revealed that ignition of mixture occurs after completion of electron gun operation.Data obtained have confirmed effectiveness of electron beam application for ignition of hydrogen and natural gas.The numerical simulation of the combustion of mixture in channel was carried out by means of ANSYS CFD 12.0 instrumentation on the basis of Reynolds averaged Navier-Stokes equation using SST/k-ωturbulence model.For combustion modeling,a detailed kinetic scheme with 38 reactions of 8 species was implemented taking into account finite rate chemistry.Computations have shown that the developed model allow to predict ignition of a mixture and flame propagation even at low flow temperatures.

Skin Friction Gage for Measurements in Hypersonic Flow

A description and results of tests of a new small-scale gage for direct measurement of skin friction force are presented in the paper.The gage design provides separated measurement of longitudinal and transversal component of friction force.Application of this scheme provides high sensitivity and necessary high-frequency response of the gage.The tests of the gage were carried out in a blow down wind tunnel at Mach numbers of 2 and 4 within the range of Reynolds numbers Rex from 0.8 to 5 million and in the hot-shot wind tunnel at Mach number 6 and Reynolds numbers Rex=2.5-10 million.The measurements of skin friction were carried out on a flat plate and on a ramp beyond the shock wave.Simultaneously with the direct measurement of friction in the blow down wind tunnel,the measurements of profiles of average velocities and mass flow rate pulsations were realised.Analysis of measurement errors has shown that the friction gage permits to measure skin friction coefficient on a flat plate with mistake not more than 10%.

Ignition Process Evolution at High Supersonic Velocities in Channel

The results of experimental research of multi-injector combustors in the regime of the attached pipe are presented.As a source of high-enthalpy working gas (air), hot shot wind tunnel IT-302M of ITAM, the Siberian Branch ofthe Russian Academy of Sciences was used. Tests have been carried out at Mach numbers 3,4 and 5, in a range ofchange of total temperature from 2000K up to 3000K and static pressure from 0.08MPa up to 0.23MPa. Injectorsection has been manufactured in two versions with a various relative height of wedge-shaped injectors with parallelfuel injection. Influence of conditions on the entrance of the combustion chamber on ignition and a stablecombustion of hydrogen was investigated. Intensive combustion of hydrogen has been received only at Machnumbers 3 and 4. Advantage of injector section with the greater relative height of injectors is revealed. Themechanism of fuel ignition in the combustion chamber of the given configuration was investigated: two-step ignitionprocess including 'kindling' and intensive combustion over all channel volume.