Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
46
4
2015
CONGRATULATIONS TO SERGEI LEONIDOVICH CHERNYSHEV ON HIS 60th BIRTHDAY!
307-308
10.1615/TsAGISciJ.2015015342
Chernyshev
MODELING OF THE LAMINAR−TURBULENT TRANSITION ON A SWEPT AND STRAIGHT WINGS WITH THE USE OF NUMERICAL SOLUTIONS OF THE NAVIER−STOKES EQUATIONS
309-322
10.1615/TsAGISciJ.2015015524
Valery Viktorovich
Vozhdaev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Andrey Filippovich
Kiselev
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky str., Zhukovsky, Moscow region, 140180 Russia
Dmitry Sergeevich
Sboev
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky str., Zhukovsky, Moscow region, 140180 Russia
Leonid Leonidovich
Teperin
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180, Russia
Sergei Leonidovich
Chernyshev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia
low-level turbulence wind tunnel
wing
laminar-turbulent transition
computational fluid dynamics
turbulence model
Application of the state-of-the-art turbulence model based on the transport equation for the intermittency
in calculating the position of laminar-turbulent transition on the swept wing surface is investigated. The theoretical characteristics of the laminar-turbulent transition for straight and swept wings with LV6 airfoil are compared. The comparative analysis of the results of calculation of boundary layer characteristics and the data of tests in a T-124 low-level turbulence wind tunnel of TsAGI is performed.
INFLUENCE OF SMALL SPATIAL PERTURBATIONS OF A SUPERSONIC FLOW ON PRESSURE AND HEAT FLUX TOWARDS A CYLINDER SURFACE
323-343
10.1615/TsAGISciJ.2015015340
Ivan Vladimirovich
Egorov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Vladimir Viktorovich
Shvedchenko
Central Aerohydrodynamic Institute (TsAGI) , Zhukovsky, Moscow region, Russia
small perturbations
pressure
heat flux
The dependence of pressure and heat flux perturbations towards the cylinder on the period of spatial perturbations of different types and different forms of supersonic flow at various Reynolds numbers, Mach numbers, and temperature factors has been studied on the basis of the numerical
solution of the Navier-Stokes equations with application of high-resolution grids for the shock wave front
SPECIAL SOLUTIONS FOR SUPERSONIC FLOW OF AN IDEAL GAS AROUND THE V-SHAPED WING WITH FLOW SEPARATIONS
345-355
10.1615/TsAGISciJ.2015015343
Renat Yamilovich
Tugazakov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
V-shaped wing
ideal gas
vortex
separation
Richtmyer-Meshkov instability
Kelvin-Helmholtz instability
Conditions for the separation of asymmetric flow of an ideal gas from a V-shaped wing with supersonic leading edges (conical flow) have been investigated. It has been shown analytically and numerically for high angles of attack and sideslip angles that the flow separation occurs in the region where a local pressure maximum takes place and the Ferri vortex singularity floats up.
New solutions have been obtained numerically in the case of symmetric flow around a wing at a high angle of attack, when gas surge in the form of a jet takes place at the intersection point of contact discontinuities upward from the central axis. The explanation of the phenomenon is given.
CORRELATION OF FLOW IN THE HYPERSONIC GRAD BOUNDARY LAYER
357-364
10.1615/TsAGISciJ.2015015398
Albert Leonidovich
Ankudinov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russia
hypersonic flow
kinetic boundary layer
Grad approximation
two-dimensional problem
thin body
translational nonequilibrium
A two-dimensional rarefied gas flow in a hypersonic kinetic boundary layer near a thin body is considered in the approximation of the gas-kinetic Grad model taking into account the strong translational nonequilibrium of the flow. The class of the variables is formulated, in which the new kinetic problem under investigation with increased complexity is correlated with the wellstudied
equivalent problem of the hypersonic Navier-Stokes boundary layer. A method for representing the solution to the Grad hypersonic kinetic boundary-layer problem on the basis of the traditional Navier-Stokes hypersonic boundary-layer solution is described. It is shown that the shear stress and the specific heat flux on the wall in the kinetic and Navier-Stokes boundary layers, respectively, coincide.
ESTIMATION OF OPERATING CONDITIONS OF A MID-RANGE AIRCRAFT AUXILIARY POWER UNIT WITH RECEIVER INLET IN TURBULENT FLOW
365-393
10.1615/TsAGISciJ.2015015341
Evgenii Petrovich
Bykov
Irkut Corporation, 68 Leningradsky Ave., Moscow, 125315,
Russian Federation
Egor Vyacheslavovich
Kazhan
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky St., Zhukovsky, Moscow Region, 140180 Russia
Vladimir Fedorovich
Tretyakov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
auxiliary power unit
receiver
flap
computational aerodynamics
SVS-2 wind tunnel
EWT-TsAGI software package
boundary layer
nonuniform flow stagnation
A series of computational and experimental studies are performed in order to estimate the characteristics
of the receiver air inlet of an advanced mid-range aircraft. The air inlet design includes two flaps deflected at an angle of 30°. The computational and experimental results are obtained for one of the most critical flight regimes at M = 0 (H = 0). The recently developed technique called EWT−TsAGI provides a high accuracy of the computational results for the model studies in spite of the flow separation near the components of the receiver air inlet. Good agreement of computational and experimental data is shown (the model scale is 1:6.5). Special attention is given to the characteristics of the air inlet in the case of the fail to open flaps and their damage. The flow parameters near the auxiliary power unit are analyzed in the cruise
flight regime at M ≈ 0.8. An algorithm for estimating the total pressure loss at the inlet to the engine is developed.
HEURISTIC MODEL OF NONSTEADY LONGITUDINAL AERODYNAMIC CHARACTERISTICS AT HIGH ANGLES OF ATTACK
395-409
10.1615/TsAGISciJ.2015015508
Petr Viktorivich
Kuzmin
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russia
Boris Alekseevich
Meleshin
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russia
Yury Fedorovich
Shelyukhin
Central Aerohydrodynamic Institute (TsAGI)
Dmitry Valeryevich
Shukhovtsov
Central Aerohydrodynamic Institute (TsAGI)
nonsteady characteristic
angle of attack
nonsteady flow
pitch moment
lift force
flow downwash
identification
Some aspects of the calculations of the longitudinal force and moment acting on a passenger airplane at high angles of attack are considered. A simplified mathematical model describing the hysteresis of aerodynamic characteristics and buffeting at high angles of attack has been developed.
The model is based on the data of aerodynamic characteristics identification by the results of regional and medium-range aircraft flight tests at M = 0.3−0.8.
The model is suitable for simulation of the aircraft dynamics at high angles of attack and allows
using nonsteady dependences of lift force and pitch moment during real-time calculations in flight simulators.