Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
42
4
2011
EXPERIMENTAL STUDY OF TANGENTIAL BLOWING EFFECT OF SUPERSONIC JET ON AERODYNAMICS OF A SUPERCRITICAL WING AT TRANSONIC SPEEDS
427-444
10.1615/TsAGISciJ.2011004141
Vsevolod Davydivich
Bokser
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region
Albert Vasilievich
Petrov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region
Petr Vladimirovich
Savin
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
wing
tangential blowing
pressure distribution
drag
lift
shock-induced separation
The results of experimental studies of tangential jet blowing efficiency for improvement of supercritical wing aerodynamics at transonic speeds are presented. The studies of the wing-fuselage model were performed in the TsAGI T-106 transonic wind tunnel in Mach number ranges of M = 0.4−0.8, Reynolds number ranges of Re = (1.4−2.2)106, and angles-of-attack α = −2°−15°. The effects of jet blowing intensity on lift, pitching moment, and drag of the model, and also on the pressure distribution at the wing middle section are examined. The values of jet momentum coefficient, required for shock-induced flow separation suppression at transonic speeds, are determined. It is shown that at Mach number M = 0.78 tangential jet blowing with low intensity (Cμ; = 0.003−0.005) increases the maximum lift-to-drag ratio values of the wing-fuselage model by 10% approximately.
NUMERICAL MODELING OF THREE-DIMENSIONAL FLOWS OF VISCOUS GAS IN NOZZLES
445-465
10.1615/TsAGISciJ.2011004142
Anatoliy Pavlovich
Mazurov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
viscous gas
three-dimensional nozzle
difference scheme
numerical computation
momentum losses
thrust losses
A technique for numerical modeling of turbulent gas flows in three-dimensional nozzles of an arbitrary shape is developed on the basis of the Reynolds-averaged Navier-Stokes equations written in thin-layer approximation relative to curvilinear coordinates. A two-parameter κ − ε turbulence model, taking into account the wall effect, is employed for computation of the turbulent viscosity. Numerical integrating of motion equations is performed using an implicit difference scheme of the third-order approximation of convection terms. Examples of computations of flow fields in three-dimensional nozzles with different cross-sectional shapes (circular, rectangular, and triangular) are presented. Results of numerical computations are compared with experimental data.
AERODYNAMIC DESIGN OF AN AIR VEHICLE IN A DIAMOND-SHAPED PLANFORM
467-478
10.1615/TsAGISciJ.2011004143
Valerii Vladimirovich
Lazarev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
Alexander Alekseevich
Pavlenko
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
Alexander Anatolyevich
Razov
Monitor Soft Ltd., P.O.B. 6006 Zhukovsky, Moscow Region, 140187, Russia
Leonid Leonidovich
Teperin
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
Ludmila Nikolaevna
Teperina
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
design
aerodynamic surface
"flying wing"
finite-difference grid
The problem of the aerodynamic design of an air vehicle in a diamond-shaped planform with a "flying wing" configuration is considered. The wing airfoil has been analytically specified in five supporting sections through main geometric parameters. Rational values of maximum thickness position and angle of the upper surface at the trailing edge are defined, enabling achievement of a maximum lift-to-drag ratio with a 3% margin of stability and lack of trim losses. A comparison of the computed and experimental aerodynamic coefficients for the model of the designed configuration is presented.
THE EFFECT OF NOSE SHAPE ON THE AERODYNAMIC DRAG OF A HIGH-SPEED AIR VEHICLE WITH A CONICAL STABILIZER
479-493
10.1615/TsAGISciJ.2011004144
Alexander N.
Kravtsov
Central Aerohydrodynamic Institute named after Prof. N.Ye. Zhukovsky (TsAGI)
Tatiana Yurievna
Melnichuk
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky, 140180, Russia
supersonic flow
axisymmetrical flow
conical stabilizer (flare)
flare semi-apex angle
hollow cylinder
spherical bluntness
wave drag
This paper presents a numerical simulation of supersonic flow around a vehicle with various noses (hollow cylinder, cone, and spherical bluntness) and the same tails (cylinder-conical stabilizer). Analysis of flow fields and space distributions of the gas-dynamic parameters in the flow and on the surface of the considered configurations is carried out. The calculated results and the experimental data are compared. The features of supersonic flow concerning the aerodynamic drag of a configuration that has a truncated cone as a stabilizing device are considered.
ALGORITHM FOR INITIATION OF LAMINAR-TURBULENT TRANSITION IN NUMERICAL SIMULATION OF FLOW ON THE BASIS OF RANS EQUATIONS
495-514
10.1615/TsAGISciJ.2011004150
Vladimir Viktorovich
Vlasenko
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Morozov
Alexander
TsAGI
computational fluid dynamics
RANS equations
boundary layer
laminar-turbulent transition
semi-empirical turbulence model
This paper is devoted to development of the "transition initiator" numerical algorithm, which may be used in calculations of flows with boundary layers on the basis of RANS equations. This algorithm "switches off" the source terms of the turbulence model upstream from the surface, where the laminar-turbulent transition begins, and gradually "switches them on" downstream from this critical surface. The quest for a satisfactory version of such an algorithm is described. For each version of the initiator, a brief description of the basic ideas is given, and the reasons for rejection of each intermediary version are explained. Also, a stable algorithm for estimation of boundary layer thickness in non-uniform flows is described.
APPLICATION OF THE GIBBS THERMODYNAMIC POTENTIAL TO DETERMINE THE COMPLETENESS OF FUEL COMBUSTION BY THE GAS-DYNAMIC METHOD
515-531
10.1615/TsAGISciJ.2011004151
A. V.
Kudryavtsev
Central Institiute of Aviation Motors (CIAM), Aviamotornaya ul. 2, Moscow, 111116 Russia
M. S.
Tararyshkin
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180 Russia
Vladimir Alekseevich
Stepanov
Central Institute of Aviation Motors (CIAM), 2 Aviamotornaya Str., Moscow,
111116, Russian Federation
combustion chamber
fire tests
Gibbs
thermodynamic potential
calculation method
experiment
A technique for experimental data processing obtained during fire tests of a combustion chamber, working on kerosene, is stated. The method for the solution of an inverse problem of the design parameter definitions for combustion chambers through the results of bench tests is offered. The problem solution is based on the joint solution of the equations for the gas dynamics and thermodynamics of complicated systems of ideal gas.
INVESTIGATION OF HEAT CONDUCTIVITY OF POROUS THERMAL INSULATION MATERIALS AT HIGH TEMPERATURES
533-542
10.1615/TsAGISciJ.2011004152
Leonid Yakovlevich
Paderin
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky, 140180, Russia
Boris Viktorovich
Prusov
Central Aerohydrodynamic Institute (TsAGI), Russia
Oleg Dmitrievich
Tokarev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky, 140180, Russia
heat insulated materials
temperature
heat flux
effective heat conductivity
This paper is dedicated to the improvement of the method and facility modernization for increasing the maximum temperature in investigations of heat conductivity of porous thermal insulated materials. In the framework of facility modernization a new measuring device is developed using modern high-temperature materials. These actions permitted us to increase the maximum temperature of the test samples at the measurements of the effective heat conductivity coefficient from 1500 K up to 1825 K. The measurements were performed under vacuum and gaseous media conditions in the pressure range of p =1− 105 Pa. The test results are presented as the temperature and barometric functions of effective heat conductivity of the investigated materials.
SOLUTION METHOD FOR MULTIPARAMETRICAL PROBLEMS OF AEROELSTICITY BASED ON SIMULARITY THEORY
543-553
10.1615/TsAGISciJ.2011004153
Vyacheslav Vladimirovich
Lyschinsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Valeriy Arkadievich
Mosunov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
Anatoliy Alekseevich
Rybakov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
flutter
multiparametrical investigation
fuselage flutter mode
stand
similarity theory
A solution method for multiparametrical problems based on similarity theory, application of the method to fuselage flutter mode investigations, explanation of its allowability in investigations of stand applications, and reduction of wind tunnel flutter simulation test work hours are considered in this paper.