Nonstationary interaction of a supersonic flying object with extended low-density regions in the atmosphere

A three-dimensional numerical model is developed and the aerodynamic loads are determined for the three-dimensional flow acting on a blunt cone flying in the atmosphere along the boundary of a rarefied region, as functions of the degree of immersion of the surface of the body in low-density air. The nonstationary gas-and aerodynamic processes accompanying the entry and exit of the body from the rarefied region are studied. The aerodynamic coefficients obtained with an approximate model are compared with the three-dimensional calculations and found to be in satisfactory agreement with them. Zh. Tekh. Fiz. 68, 32–37 (November 1998)     

Prediction of aerodynamic noise reduction by using open-cell metal foam

As the speed of high-speed train (HST) increases continuously, aerodynamic noise has become more remarkable compared with the wheel/rail noise, which affects the inhabited environment along the railway and the riding comfort. This paper preliminarily investigates the feasibility of using open-cell metal foam covering layer to reduce the low Mach number aerodynamic noise generated by the flow around a circular cylinder which is the typical section of pantographs. The aerodynamic noises radiated from the circular cylinder with and without metal foam are calculated. The hybrid method combining two-dimensional large eddy simulation (LES) with Ffowcs Williams–Hawkings (FW–H) equation is employed. The calculated Strouhal number, time-averaged drag coefficient, base pressure and overall sound pressure level agree well with some available experimental data. Then, the influences of metal foam porosity, pore density, thickness of covering layer and the speed of train on the aerodynamic noise and the aerodynamic forces are investigated, and some detailed comparisons of flow field are made. The numerical results indicate that as a passive scheme, the open-cell metal foam with high porosity can modify the flow, adjust the vortex shedding frequency and regularize the wake, leading to a significant reduction of aerodynamic noise. The results are expected to provide useful information for the control of aerodynamic noise using this new material.     

Determination of the temperature distribution in liquids and solids using holographic interferometry

It is shown that holographic interferometry can be applied to solve two problems: heating of a glass plate by a complex heat source and nonisothermal flow of a submerged jet around a wedge. The process of isolating and numbering the skeletal lines on the interferograms is automated and direct calculations are made of the temperature fields. Zh. Tekh. Fiz. 69, 106–111 (June 1999)     

Experimental investigation of nanosecond discharge plasma aerodynamic actuation

In this paper we report on an experimental study of the characteristics of nanosecond pulsed discharge plasma aerodynamic actuation. The N 2 (C 3 Π u ) rotational and vibrational temperatures are around 430 K and 0.24 eV, respectively. The emission intensity ratio between the first negative system and the second positive system of N 2 , as a rough indicator of the temporally and spatially averaged electron energy, has a minor dependence on applied voltage amplitude. The induced flow direction is not parallel, but vertical to the dielectric layer surface, as shown by measurements of body force, velocity, and vorticity. Nanosecond discharge plasma aerodynamic actuation is effective in airfoil flow separation control at freestream speeds up to 100 m/s.     

钝锥再入飞行器黏性干扰效应建模

针对典型的钝锥外形, 采用统一气体动理学格式(UGKS)模拟了高度70~110 km下不同Mach数和攻角的流场, 进行了流场特性的分析, 并基于黏性干扰的理论成果, 将气动力特性与第3黏性干扰参数、攻角和Mach数等参数进行关联, 建立了气动力系数的黏性干扰模型, 给出了模型预测结果的相关性分析和准确性评估。经初步测试, 该模型预测结果与UGKS直接模拟结果具有良好的一致性, 对工程应用快速获取高空气动特性具有重要意义。      

On the minimum drag of a supersonic high-speed air vehicle with a conical stabilizer

The parameters of a conical stabilizer and its effect on the aerodynamic characteristics of the high-speed air vehicle, in general, are examined. The flow characteristics of an high-speed air vehicle with a conical stabilizing device are analyzed. Simulation results are compared with experimental data. Qualitative features of the supersonic flow associated with the characteristics of the drag of an aerodynamic configuration with a stabilizing device in the form of a truncated cone are considered. Particular attention is paid to the physical aspects of the flow around the considered configurations and to elucidating the mechanisms responsible for a minimum in the drag coefficient of a wingless high-speed air vehicle. A general mechanism of occurrence of the minimum in the drag coefficient for aerodynamic configurations with a conical tail stabilizer is studied.     

On the aerodynamic mechanism of torsional flutter of bluff structures

This paper is concerned with theoretical and experimental investigations on the aerodynamic mechanism of torsional flutter of bluff structures. In the experiment, measurements were made of the unsteady aerodynamic lifts and moments acting on two rectangular bar models which were forced to oscillate either in a torsional or in a heaving mode in a uniform wind tunnel flow. It is found that the fluid memory effect is, in marked contrast to the situation for transverse galloping, responsible for the onset of torsional flutter of bluff structures. The effect of the pivotal position on torsional flutter of bluff structures is also investigated.     

Aerodynamic sound production in low speed flow ducts

Measurements of spoiler aerodynamic noise, generated in a low velocity flow duct and radiated from an open exhaust termination, have been made in the form of sound power spectra. The individual $\text{1}\text{3}$ octave power measurements are satisfactorily collapsed (within ± 3 dB) with the aid of derived theoretical scaling laws. Non-dimensional spectra are presented which permit generalized predictions of flow noise for bluff bodies, including splitter attenuators, mounted in low speed flow ducts.     

Adjoint-based error estimation and adaptive mesh refinement for the RANS and k–ω turbulence model equations

In this article we present the extension of the a posteriori error estimation and goal-oriented mesh refinement approach from laminar to turbulent flows, which are governed by the Reynolds-averaged Navier–Stokes and k–ω turbulence model (RANS-kω) equations. In particular, we consider a discontinuous Galerkin discretization of the RANS-kω equations and use it within an adjoint-based error estimation and adaptive mesh refinement algorithm that targets the reduction of the discretization error in single as well as in multiple aerodynamic force coefficients. The accuracy of the error estimation and the performance of the goal-oriented mesh refinement algorithm is demonstrated for various test cases, including a two-dimensional turbulent flow around a three-element high lift configuration and a three-dimensional turbulent flow around a wing-body configuration.     

Aerodynamic measurement of a large aircraft model in hypersonic flow

Accurate aerodynamic measurements in the hypersonic flow of large aircraft models in tunnels have practical significance, but pose a significant challenge. Novel aerodynamic force measurement methods have been proposed,but lack theoretical support. The forms of the force signals techniques for signal processing and calculation of aerodynamics are especially problematic. A theoretical study is conducted to investigate the dynamic properties based on models of the draw-rod system and slender rods. The results indicate that the inertia item can be neglected in the rod governing equation;further, the solutions show that the signals of each rod are a combination of aerodynamic signals(with a constant value) and sine signals, which can be verified by experimental shock tunnel results. Signal processing and aerodynamics calculation techniques are also found to be achievable via the flat part of the signals.     

Noise Sources of Aerodynamic Origin in Air Blowers

The paper presents the results of theoretical and experimental studies of the occurrence and locations of aerodynamic noise sources in air blowers related to air flow around stationary and moving elements inside a machine body. These studies were based on basic research by Lighthill and Curle and used a developed method for measuring pressure pulsations on rotating blades and stationary elements of a machine body. The most significant sources of discrete and broadband components of aerodynamic noise were revealed. The role of blades in an impeller in the emission of discrete noise components was studied. It was established that broadband peaks in the emitted noise are associated with acoustic resonances of the internal volume of the air blower. It was shown that the turbulence and velocity of the incoming flow influence the intensity of aerodynamic sources inside the body. Our studies spurred both deeper research into the nature of aerodynamic noise sources that form in air blowers and recommendations for reducing the noise produced by these sources.     

Experimental studies on the interaction of jets with the vortex wake of slender bodies

An experimental study has been conducted to examine the low-speed aerodynamic characteristics of a pair of circular jets behaviour in the vortex-wake of a blunted cone cylinderbody combination with and without a 70° leading edge sweep delta wing. The induced flow-field was examined via two-dimensional hot-wire anemometry surveys. Comparisons were made between the induced wake with and without the circular jets. The flow field over the models was visualized using smoke and oil flow visualization. The jet-pair was found to undergo severe distortion within a very short distance from the nozzle exits. The shape of the jets was shown to change considerably when placed in the vortex wake flow field of the models, which caused the jet-pair to spread and become entrained within the vortices and wake created by the models.     

Duality in two-dimensional Z(N)-symmetric spin models on a finite lattice

We propose a method for deriving duality relations for two-dimensional inhomogeneous Z(N)-symmetric models on a finite square lattice wound around a torus. The method is used to obtain duality relations for the vector Potts model, the Berezinskii-Villain Z(N)-model, the Ashkin-Teller model, and the 8-vertex model on a lattice obliquely wound around a torus, as well as an exact relation linking the partition functions of the latter two models. Zh. éksp. Teor. Fiz. 113, 240–260 (January 1998)     

Nonequilibrium Radiation Aerothermodynamics of the Command Modulus of Apollo 4 at Altitudes above 75 km

The problem of the radiation gas dynamics of super-orbital entry into dense layers of the Earth’s atmosphere of the command module of Apollo 4 is solved numerically in the two-dimensional formulation of the flow around an aerodynamic frontal shield at the velocity V∞= 10.7 km/s in the altitude range H = 91.5?76.2 km. The density distributions of the spectral and integral radiation heat fluxes on the surface flowed around are obtained. The considerable role of atomic spectral lines in the radiation heating of the surface is shown. The results of calculations are compared with the flight experimental data and the calculated data of other authors.     

New Mathematical Models for Particle Flow Dynamics

Abstract

A new class of integro-partial differential equation models is derived for the prediction of granular flow dynamics. These models are obtained using a novel limiting averaging method (inspired by techniques employed in the derivation of infinite-dimensional dynamical systems models) on the Newtonian equations of motion of a many-particle system incorporating widely used inelastic particle-particle force formulas. By using Taylor series expansions, these models can be approximated by a system of partial differential equations of the Navier-Stokes type. The exact or approximate governing equations obtained are far from simple, but they are less complicated than most of the continuum models now being used to predict particle flow behavior. Solutions of the new models for granular flows down inclined planes and in vibrating beds are compared with known experimental and analytical results and good agreement is obtained.     

Flying characteristics and flow pattern of a sphere with dimples

It is known that the flying characteristics of the golf ball is influenced by flying speed, rotational frequencies and the dimples, etc. In this study, the drag and lift acting on the test balls are measured using a three components loadcell by changing Reynolds number and the spin rate ratio, the number and the depth of dimples. And the flow around the balls is visualized by applying the oil film method and PIV in the stationary state. From these results, the aerodynamic drag and lift coefficients of the balls in the stationary and the rotational state are made clear.     

Development of the method of an electrohydrodynamic force effect on a boundary layer for active control of aerodynamic flows

The results of investigations on the possibility of an electrohydrodynamic force effect on a gas flow implemented with the help of a barrier discharge are presented. A new method of controlling the laminar flow around a base with suppression of instabilities of the incoming flow due to electrohydrodynamic force action on the boundary layer near the forward edge of a swept wing is proposed. An efficient multidischarge actuator system is developed and created for active control of aerodynamic flows with induced-air-flow characteristics exceeding the world analogues.     

Design of supersonic three-dimensional inlets using two-dimensional isentropic compression flow

The design of supersonic three-dimensional inlets using the V-shaped body forming a two-dimensional flow including an initial oblique shock wave and a subsequent isentropic compression wave is considered. Such a flow appears attractive for inlets design due to a possibility of obtaining high compression levels of external flow over the inlet ramp with small losses of the total pressure. Numerical computations of the flows around the designed configurations were carried out in design and off-design regimes using Euler code. The flow structure was identified, the aerodynamic characteristics of the inlets were determined. The investigation covers the range of supersonic speeds corresponding to the freestream Mach numbers M_∞= 1.8−2.5.     

关于叶轮机时均(准四维)和非定常(四维)气动设计体系的初步诠释

本文以考虑非定常流动的完整性为线索,总结概述了先前气动设计体系的困难与限制,在此基础上,以描述叶轮机流动的时均和时间精确模型为核心分别从其构成和标志性技术对叶轮机时均和非定常气动设计体系进行了初步诠释。文章认为促成时均(准四维)和非定常(四维)气动设计体系现实应用是叶轮机发展的最后契机。