Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
44
3
2013
ABOUT INCREASE OF EFFICIENCY OF PLASMA MULTI-ACTUATOR SYSTEM FOR BOUNDARY LAYER CONTROL
305-326
10.1615/TsAGISciJ.2013009688
Alexander Petrovich
Kuryachii
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region
Dmitriy Anatolyevich
Rusyanov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky, 140180, Russia
Sergei Leonidovich
Chernyshev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia
Vladimir Vladimirovich
Skvortsov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
dielectric harrier discharge
plasma actuator
energy efficiency of an actuator
numerical simulation
The numerical simulation of spatial-periodic systems of electrogasdynamic actuators (plasma actuators), using the dielectric barrier discharge (DBD) for a volumetric force impact on a gas flow was carried out. Both the typically used design of actuators and the advanced design with an additional screening electrode are considered. The mathematical model of the dielectric barrier discharge in air was formulated in the drift-diffusion approximation without accounting for convective transfer of the charged particles. The following volumetric reactions are taken into consideration, namely, the ionization of nitrogen and oxygen by electron impacts, the attachment of electrons to oxygen, the detachment of electrons from negative ions, and the ion-ion and the electron-ion recombination. The two types of boundary conditions were considered at the open dielectric surface, namely, the model of instantaneous recombination and the model of finite rates of recombination and electron desorption. The numerical simulation both for the typical and for the advanced actuator systems was done with the same set of problem parameters. It was shown that the advanced scheme provides the better energy efficiency of the system of DBD actuators. It was also found that the main integral characteristics of the DBD actuator weakly depend on the type of boundary conditions used on the dielectric surface. The new simplified design of a system of DBD actuators was proposed.
SELECTION OF VISCOUS TERMS APPROXIMATION IN DISCONTINUOUS GALERKIN METHOD
327-354
10.1615/TsAGISciJ.2013009684
Aleksey Igorevich
Troshin
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
Vladimir Viktorovich
Vlasenko
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Andrey Viktorovich
Wolkov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
discontinuous Galerkin method
convection-diffusion equation
accuracy order
The implicit discontinuous Galerkin method is presented for solving the two-dimensional model scalar convection-diffusion equation. Three approximations of diffusion terms are considered, which have been named Bassi & Rebay 1, Cockburn & Shu, and Bassi & Rebay 2. The results of the test computations are reported and accuracy order estimates are found. The influence of point discontinuities in boundary conditions on convergence rate to the exact solution is analyzed. Recommendations on choice of diffusion terms approximation are given.
AERODYNAMIC LOADS MEASUREMENTS ON AN AIRFOIL USING PIV SYSTEM
355-370
10.1615/TsAGISciJ.2013009699
Vadim Anatolyevich
Vlasov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky str., Zhukovsky, Moscow region, 140180 Russia
Gadzhi Gadzhimagomaevich
Gadzhimagomedov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Vladimir Mikhaylovich
Lutovinov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
Dmitry Sergeevich
Sboev
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky str., Zhukovsky, Moscow region, 140180 Russia
wind tunnel
velocity field
laser sheet
nonintrusive measurements
PIV system
aerodynamic loads
lift coefficient
drag coefficient
airfoil
An assessment of applicability of using PIV-velocity data for the nonintrusive aerodynamic force characterization (lift and drag) of an airfoil is made. The method of the control volume based on integration of hydrodynamic variables along the closed contour around an airfoil was used for calculations. The results of these calculations were compared with results of standard pressure-based lift coefficient measurements (surface pressure distribution and wake rake).
SOLUTION OF THE INVERSE PROBLEM FOR AN AIRFOIL WITHIN THE FRAMEWORK OF THE REYNOLDS AVERAGED NAVIER-STOKES EQUATIONS
371-385
10.1615/TsAGISciJ.2013009695
Anatoliy Longinovich
Bolsunovsky
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
Nikolay Petrovich
Buzoverya
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
Irina Anatolyevna
Gubanova
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
Maria Anatolyevna
Gubanova
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
inverse problem
Navier-Stokes equations
ANSYS CFX
airfoil
pressure distribution
A new iterative method for solution of the inverse airfoil problem in a compressible gas flow within the framework of RANS equations has been developed. The method belongs to the class of residual correction methods. An airfoil geometry correction, decreasing the residual between the computed and desired pressure distributions, is defined by means of a correction block based upon the previously developed domestic inverse full-potential code. Several examples of inverse problem solution showing high efficiency of the method are given.
ENGINEERING TECHNIQUE OF CORRECTING THE MAXIMAL LIFT COEFFICIENT OF MODELS FOR THE FULL-SCALE FLIGHT CONDITIONS
387-404
10.1615/TsAGISciJ.2013010128
Gennadiy Andreevich
Fedorenko
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
maximal lift coefficient
influence of Reynolds number
initial degree of free-stream turbulence
surface roughness
correcting for the full-scale flight conditions
Results of experimental research of models of lifting surfaces (airfoil sections, half-wings, aircraft configurations) in wind tunnels (WTs) are analyzed for influence of Reynolds number, initial degree of flow turbulence, and roughness of model surface on the maximal lift coefficient CLa max. It is shown that, on one hand, the maximal lift coefficient of an aircraft in full-scale flight cannot exceed maximal threshold CLa max ∞ obtained for an aerodynamically smooth model in WT, and, on the other hand, it cannot be lower than minimal threshold CLa max(min)∞ obtained for a completely turbulent boundary layer over a model. The technique of correcting the maximal lift coefficient CLa max of models for the full-scale flight conditions is presented in this work.
THE METHOD OF OPTIMAL PROFILING OF FLYING VEHICLE FUSELAGE AND NOZZLE AT THE CRUISING SUPERSONIC FLIGHT
405-417
10.1615/TsAGISciJ.2013010195
Anatoliy Pavlovich
Mazurov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
Sergey Alexandrovich
Takovitskii
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovskystr., Zhukovsky, 140180, Moscow region, Russia
optimization
objective function
fuselage forebody
nozzle
lift
flying vehicle trim
The method of profiling of elements of a high-speed flying vehicle airframe and power plant nozzle is presented. The lift at the cruising flight is chosen as the objective function, which is maximized under external dimensions constraints and isoperimetric condition on the pitch moment. The direct optimization method is used, which combines the flow modeling within the framework of the Euler equations and the Newton minimization algorithm. The results of elementwise optimization and complex optimization which strengthens the positive effects of integration are compared. Analysis of total aerodynamic loads on the optimal configurations is performed.
GENERATION OF THE ALGORITHM OF SYNCHRONIZATION OF RELAY-HYSTERETIC ELEMENTS IN DIGITAL REDUNDANT CONTROL SYSTEM BY MEANS OF FINITE STATE AUTOMATION
419-432
10.1615/TsAGISciJ.2013009686
Sergey Georgievich
Bazhenov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, Moscow region, 140180 Russia
digital system
redundancy
synchronization
control axes
relay
hysteresis
finite automation
The present work proposes a method for synchronization of states of the control axes' discrete elements and for control of the two-channel self-testing computer of the modern digital control system of the aircraft. The method is based on the theory of finite automation. The algorithms of synchronization of relay and hysteresis outputs are discussed.
NONCONTACT MEASUREMENTS OF NORMAL DEFORMATION FIELDS OF A CONSTRUCTION SURFACE BY VIDEOGRAMMETRY METHODS WHILE STRENGTH TESTING
433-444
10.1615/TsAGISciJ.2013010258
Vladimir Petrovich
Kulesh
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
Sergey Mikhaylovich
Naumov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
strength testing
deformation fields
noncontact measurements
videogrammetry
A videogrammetry method using one digital camera for noncontact measurements of a distributed normal deformation of construction elements with a flat surface or having a small curvature is developed. Investigations of the surface buckling are performed at the local shell buckling of typical cylindrical fuselage panels of a passenger plane made of aluminum alloy and at the general buckling of a full-scale flat panel of a perspective aircraft wing box made of polymer composite material with a loading up to destruction. It is found that in both cases, the buckling deformation of the surface has two main modes with the opposite sign of normal deviations. The maximum deformation deviations of positive and negative modes of the panel made of aluminum alloy are +1.26 and −2.47 mm, and those of the positive and negative modes of the panel made of composite material are ±1.33 mm directly before the destruction.