Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
49
4
2018
TO THE 100th ANNIVERSARY OF TSAGI
299-307
10.1615/TsAGISciJ.2018027783
Sergei Leonidovich
Chernyshev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia
TsAGI
Zhukovsky
stages of the institute development
prospects for the future
A review of TsAGI basic activities from the instant of its foundation up to now is presented. The basic stages of the institute development and the invaluable contribution of TsAGI to aviation science during the entire century of its existence are described. Based on modern-life realities and outlined
trends, prospects of TsAGI development and international cooperation are presented.
SCIENTIFIC HERITAGE OF NIKOLAI EGOROVICH ZHUKOVSKY AVIATION
309-323
10.1615/TsAGISciJ.2018027990
G. P.
Svishchyov
Nikolai Egorovich Zhukovsky (Joukowski)
lift force
Zhukovsky theorem (Joukowski theorem)
A review of a wide range of scientific problems that were solved by Nikolai Egorovich Zhukovsky at different stages of his activity is given in this paper. His main achievements and scientific discoveries are presented. His outstanding contribution to aeronautical science is emphasized.
BASIC CONDITIONS FOR DETERMINING AIRPLANE STRENGTH WHEN FLYING IN DISTURBED AIR
325-341
10.1615/TsAGISciJ.2018027937
Alexander Ivanovich
Makarevskii
vertical air gust
airplane strength
horizontal gust
airplane load factor
disturbed air
The basic conditions that determine airplane strength during flight in disturbed air are presented.
CONCEPT OF A MODERN FIGHTER
343-359
10.1615/TsAGISciJ.2018027613
Georgiy Sergeevich
Bushgens
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky, Moscow Region, 140180 Russia
Valeriy Leonidovich
Sukhanov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky, Moscow Region, 140180 Russia
fourth-generation fighter
concept of a fifth-generation fighter
combat effectiveness
The interaction of requirements and technical capabilities is considered on the example of defining the concept of the fourth-generation fighters. A brief review of the research on determining the concept of a new fifth-generation fighter conducted in the USSR, USA, and a number of other countries is given. It was shown that the concept of fighters is determined by scientific and technical achievements and can have various specific solutions. The task of each project is to find the optimal solutions in terms of high combat effectiveness at minimal cost.
PROPAGATION OF A SONIC BOOM WAVE IN A TURBULENT MEDIUM
361-371
10.1615/TsAGISciJ.2018027814
Sergei Leonidovich
Chernyshev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia
sonic boom
shock wave
geometric acoustics equations
stochastic model of uniform isotropic turbulence
N-shaped wave
Modern investigations on the influence of atmospheric turbulence on a sonic boom are considered. A method of simulating the effect of the atmospheric turbulent boundary layer on shock wave propagation is proposed. The method is based on geometric acoustics equations and a stochastic model of uniform isotropic turbulence. Capabilities of the method are demonstrated by an example of solving a model problem of propagation of a plane N-shaped wave in a stochastic field of temperature and velocity fluctuations.
ON STEADY LAMINAR FLOW OF A FLUID AROUND A BLUFF BODY AT HIGH REYNOLDS NUMBER
373-384
10.1615/TsAGISciJ.2018027757
Vladimir Vasilievich
Sychev
body drag
separated region
mixing layer
A steady plane flow of incompressible fluid around a bluff body at high Reynolds number (Re) is investigated by the method of matched asymptotic expansions. It is determined on the assumption of a nonzero drag coefficient at Re → ∞ that the separated region as a whole in the general approximation is an ellipse of a small relative thickness. Its longitudinal and transverse sizes grow proportionally to Re and Re1/2, respectively. On a body scale, the Kirchhoff model of flow with free streamlines takes place.
ABOUT THE SPECIAL FEATURE OF DURABILITY CHARACTERISTICS FOR ALUMINUM ALLOYS
385-393
10.1615/TsAGISciJ.2018027449
Andrei Fedorovich
Selikhov
Corresponding
Member of the USSR Academy of Sciences
Innokentii Evgen’evich
Ushakov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky St., 1, Zhukovsky,
Moscow Region, 140180, Russian Federation
durability of aluminum alloys
durability
stress concentrators
load
stress intensity factor
level of nominal stresses
durability curve
durability range
As a result of generalizing the experimental data on the durability of articles with stress concentrators of aluminum alloys, obtained for a pulsing loading cycle at various loading frequency application, it was found that, for each value of stress intensity factor and frequency, there is a level of nominal stresses at which all durability curves for aluminum alloys pass through the durability range comparable to the accuracy of determination of the curves. This newly obtained fact can be used for generalizing the model of scattering of durability properties, for planning a fatigue experiment, for investigating the laws of summarizing fatigue damages at programming, and for random loadings, accounting for durability scattering.
HYDRODYNAMICS OF A THIN FLEXIBLE BODY
395-401
10.1615/TsAGISciJ.2018027453
Georgii Vladimirovich
Logvinovich
hydrodynamics of a thin flexible body
fish swimming mechanism
method of plane sections
hydrodynamic characteristics of fish motion
To clarify the fish swimming mechanism, hydrodynamics of a thin deformable body is studied by the method of plane sections. Simple formulas are derived for estimating the thrust and consumed power in the case of sinusoidal wave deformations of the body axis. Hydrodynamic characteristics of fish motion are estimated. Theoretical results are compared to experimental data.
ESTIMATION OF THE LIMITING DEVIATIONS OF THE TRAJECTORY PARAMETERS OF AN AIRCRAFT DURING AUTOMATIC LANDING
403-414
10.1615/TsAGISciJ.2018027659
Vasiliy Aleksandrovich
Yaroshevsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Viktor Petrovich
Kuzmin
aircraft trajectory parameters
automatic landing
worst longitudinal wind realizations
automatic aircraft flareout
vertical speed
flight range
specified probability
A method is proposed for specifying the worst longitudinal wind realizations during automatic aircraft flareout in order to estimate the limiting deviations of its trajectory parameters (i.e., vertical speed Vy and flight range L) corresponding to a small level of specified probability (Pspec = 10-5 to 10-7) at the moment the aircraft touches the runway. The proposed technique is used to study the automatic landing of a typical passenger aircraft.
TO THE THEORY OF UNSTEADY SEPARATION AND INTERACTION OF BOUNDARY LAYER WITH SUPERSONIC GAS FLOW
415-427
10.1615/TsAGISciJ.2018027466
Igor Ivanovich
Lipatov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Vladimir Yakovlevich
Neiland
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky 140180, Russia
unsteady separation
unsteady perturbations
flap
base pressure
laminar boundary layer
asymptotic relation
boundary value problem
external supersonic flow
The effect of unsteady perturbations caused by the oscillation of the aerodynamic control surface (flap) or by the base pressure pulsations on the flow in the laminar boundary layer is analyzed. The flow regimes are classified depending on the frequency and amplitude of oscillations (pulsations) and Reynolds number. The asymptotic relation between parameters that distinguishes separated and attached flow regimes is derived. Analytical and numerical solutions of several boundary value problems that describe unsteady interaction between the flow in the laminar boundary layer and the external supersonic flow are obtained.
AIRCRAFT ENVIRONMENTAL NOISE LEVEL ESTIMATION AT LANDING APPROACH
429-436
10.1615/TsAGISciJ.2018027638
Vladimir Grigor'evich
Dmitriev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia
Valerii Fedorovich
Samokhin
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, Moscow Region, 140180 Russia
Natalia P.
Maslova
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
aircraft noise at landing
power plant
airframe
landing gear
high lift devices
Three approximate methods are proposed for the estimated noise level of an aircraft performing approach.
The noise level from the power plant is determined using existing software packages. In the first two methods, the estimation of the airframe noise level is based on modern concepts of the ratio of the acoustic noise emission from the power plant and that of the aircraft airframe, or on the known data on the relationship between the noise emissions from the chassis and the high lift devices, and the chassis noise level is calculated using known semi-empirical methods. In the third method, to estimate aircraft noise it is proposed to use experimental data on the statistically minimum environmental noise level at landing approach of an airplane with a conventional airframe layout.
MATHEMATICAL MODEL OF THE AIRCRAFT AERODYNAMICS IN A VORTEX WAKE
437-453
10.1615/TsAGISciJ.2018027647
Aleksandr Marksovich
Gaifullin
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
Yuriy Nikolaevich
Sviridenko
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
aircraft
vortex wake
neural networks
The process of the generation and evolution of the vortex wake behind an aircraft in turbulent atmosphere is considered. An artificial neural networks–based approach to the development of a mathematical model of the aerodynamics of an aircraft during in-flight refueling is proposed. The accuracy and speed of the developed software module were evaluated for the problem of in-flight refueling modeling using a ground-based flight simulator.
THE INTERACTION OF SHOCKWAVES WITH A BLUNTED PLATE
455-475
10.1615/TsAGISciJ.2018028157
Ivan Vladimirovich
Egorov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Volf Ya.
Borovoy
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, Moscow Region, 140180 Russian Federation
Vladimir Evguenyevich
Mosharov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Vladimir Nikolaevich
Radchenko
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Arkadii Sergeyevich
Skuratov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
shock waves
interaction
bluntness
boundary layer
entropy layer
separation
heat flux
pressure
measurement techniques
numerical simulation
shock wind tunnel
A review of experimental and numerical studies of the interaction of oblique shock waves with boundary and entropy layers of the blunted plate, performed by the authors, is presented. Three variants of interference flow were studied, namely, a shock wave impinging on a plate from the outside, the flow near a sharp wedge mounted on a plate, and the flow near a pair of counter wedges mounted on a plate. The strong influence of even small plate bluntness on the flow structure and heat transfer at hypersonic flow velocities is revealed. The influence of the basic gas-dynamic parameters and geometrical characteristics of the investigated structures on the nature of the interference flow and
the maximum value of the heat transfer coefficient is studied. The experiments were carried out in the UT-1M shock wind tunnel at Mach numbers M∞ = 5–10 for a wide range of Reynolds numbers and laminar and turbulent states of the undisturbed boundary layer. In addition to discrete sensors, panoramic methods for heat flux and pressure measuring were widely used. For numerical simulation of the flow, the Reynolds-averaged Navier–Stokes equations were solved using the q-ω turbulence model.