Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
40
3
2009
DEVELOPMENT OF AEROSHAPE AND INVESTIGATION OF SMALL-SIZED WINGED RE-ENTRY VEHICLE AEROTHERMODYNAMIC CHARACTERISTICS
279-298
10.1615/TsAGISciJ.v40.i3.10
Anatoliy Vladimirovich
Bobylev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
A. V.
Vaganov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Vladimir Grigor'evich
Dmitriev
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region, Russia
Sergey Mikhailovich
Zadonsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Aleksandr Yuryevich
Kireev
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
E. A.
Stepanov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Vasiliy Aleksandrovich
Yaroshevsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
re-entry vehicle
aerodynamic characteristics
lift-to-drag ratio
base drag
aerodynamic heating
radiation-equilibrium temperature
surface catalytic activity
descent trajectory
cross range
landing
equilibrium glide trajectory
The search for an efficient, small-sized winged re-entry vehicle aeroshape is considered. Problem solving involves an iteration process aimed at changing initial aerodynamic external aeroshape in order to realize given performance characteristics. The computation of aerodynamic characteristics at every iteration step is completed using software packages based on different engineering techniques. Estimation of descent trajectory parameters involves searching for the optimal trajectory, and realizing the maximum cross range at given equilibrium temperature limitations, for example, at stagnation points of aeroshape elements. For this reason the shape of perspective small-sized winged re-entry vehicle aeroshapes is worked out. The defining feature of the aeroshape is that its shape, size, and wing location provide not only balancing and stability, but also the necessary value of lift at all flight modes. The shape of the nose section, the airfoil, and the value of leading-edge sweep enabled realization of acceptable heat fluxes on the vehicle surface at hypersonic speeds.
COMPUTATION OF ICE SHAPES ON AN AIRFOIL
299-307
10.1615/TsAGISciJ.v40.i3.20
Alexander Alexandrovich
Nikolsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
airfoil
icing
aerodynamics
A procedure for the definition of trajectories and coefficients of overcooled droplets sinking on an airfoil was worked out and realized numerically for simulating the process of wing and helicopter blade icing. Similarity parameters of trajectories were specified. Computation of ice shapes on the airfoil NACA 00012 was fulfilled, and the obtained results were compared with known computational and experimental data.
EXPERIMENTAL AND NUMERICAL INVESTIGATIONS OF BOUNDARY LAYER TRANSITION ON BLUNTED CONES AT SUPERSONIC FLOW
309-319
10.1615/TsAGISciJ.v40.i3.30
Vladimir Nikolaevich
Brazhko
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
A. V.
Vaganov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
N. A.
Kovaleva
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
N. P.
Kolina
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Igor Ivanovich
Lipatov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
blunted cone
boundary layer
transition
Presented are the numerical and the experimental results describing laminar/turbulent boundary layer transition on thin blunted cones at freestream Mach numbers of M = 6.1 and 8. Shown is the common influence of cone nose bluntness, semi-angle of cones, and Mach and Reynolds numbers on the boundary layer transition. The present results, concerning the beginning of boundary layer transition, are compared with data obtained previously in wind tunnels at super- and hypersonic flows over the thin blunted cones.
COMPUTATIONAL ANALYSIS OF THE EFFICIENCY OF A PROPELLER IN A VISCOUS WAKE USING NAVIER-STOKES EQUATIONS
321-331
10.1615/TsAGISciJ.v40.i3.40
Alexander Anatolyevich
Razov
Monitor Soft Ltd., P.O.B. 6006 Zhukovsky, Moscow Region, 140187, Russia
CFD
efficiency analysis
viscous wake
propeller
Frude model
coefficient of efficiency
airship
Navier-Stokes equations
The computational analysis of the efficiency of a propeller in a viscous wake is performed. A simplified model of an airship with a stern-mounted propeller is considered as an example. Velocity field near the airship, pressure distribution, and shear stresses on the airship surface are computed for the cases of an operated propeller and a turned-off propeller. Analysis of forces acting on the airship and on the propeller is performed for the propeller mounted in an airship stern in a viscous wake and for the propeller located out of the airship interaction zone. The power required for the cruise flight is shown to be approximately 7.5% less in the first case.
METHOD FOR DETERMINATION OF AXIAL COMPRESSOR PARAMETERS AT THE BASIC POINTS OF STALLING BRANCH CHARACTERISTICS
333-353
10.1615/TsAGISciJ.v40.i3.50
Leonid Dmitrievich
Kolesinsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
R. M.
Fedorov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
axial compressor
flow coefficient
flow separation zone
hysteresis
stall boundary
in-stall branch of compressor characteristic
Presented in this work is a method for calculation of compressor characteristics at a fully developed rotating stall regime with a single flow separation zone covering the entire height of the annular duct of the compressor flow at a constant rotational speed. The method enables sufficiently accurate prediction of the compressor parameters πk and ηk on the left (stalling) branch of the compressor characteristics, including the points of the stall end boundary, as a function of the flow coefficient, the angle extension of stall zone, and of the pressure ratio at the stall point on the right (nonstalling) branch of the characteristic. The method also ascertains the dimension of the hysteresis loop. The extension of the stall zone is shown to be the significant parameter determining the compressor performance at the stall regime.
THE APPROXIMATION OF THE STANDARD ATMOSPHERE MODEL
355-365
10.1615/TsAGISciJ.v40.i3.60
Vasiliy Aleksandrovich
Yaroshevsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
atmosphere density model
mathematical simulation
vehicle entry into Earth's atmosphere
simplified exponential model
A model of atmospheric density dependence on altitude, convenient for fulfillment of the mathematical simulation of space vehicle entry into Earth's atmosphere, is proposed. Discussed are questions concerning the possibility of replacing this model with a simplified exponential model.
VIBRATIONS AND ACOUSTIC RADIATION OF THIN-WALLED STRUCTURES AT NONUNIFORM AEROACOUSTIC EXCITATION
367-378
10.1615/TsAGISciJ.v40.i3.70
Boris Maksimovich
Efimtsov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180 Moscow region
Aleksander Yakovlevich
Zverev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180 Moscow region
vibrations
acoustic radiation
thin-walled structures
aero-acoustic excitation
nonuniform field
One- and two-dimensional vibrations of bound thin-walled structures excited by the spatially nonuniform convective field of random pressure fluctuations are studied. Expressions for the spectral density of generalized forces for sinusoidal forms of elastic system vibrations are obtained, and expressions are developed for estimation of the vibrational energy and power of the thin-walled structure sound radiation, depending on the characteristic parameters of the excitation field. General principles of the vibrations and of the acoustic radiation of the bound and unbound elastic systems are established.
ROPE SYSTEM PARAMETRIC CONFIGURATION FOR AIRCRAFT TOWING WITH GUARANTEED VERTICAL SHIFT RANGE
379-391
10.1615/TsAGISciJ.v40.i3.80
Lev Vladimirovich
Morozov
Samara State Aerospace University, Moskovskoye Shosse 34, 443086, Samara, Russia
airplane
rope system
towing
Steady motion of a low-sized vehicle connected via flexible rope to a horizontally flying airplane-carrier is considered. Rope system parameters are determined to provide the maximum range of vertical shifts of the apparatus relative to the carrier in the entire region of the carrier's horizontal flight regimes.
DESIGN OF A MULTIPURPOSE AEROELASTIC MODULAR MODEL
393-399
10.1615/TsAGISciJ.v40.i3.90
V. A.
Malyutin
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
aeroelasticity
elastically scaled aerodynamic model
A multipurpose aeroelastic modular model of the lift surface of a high-aspect-ratio aircraft is considered. A beam structural scheme is used for the simulation of model stiffness characteristics. An algorithm for the determination of model design parameters based on the requirement of stiffness characteristic similarity is proposed. Design results for the elastically scaled model of a high-aspect-ratio wing are presented.