Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
40
5
2009
STUDY OF AERODYNAMICS OF THE AEROSPACE VEHICLE WITH A DEFLECTED BALANCING FLAP
517-534
10.1615/TsAGISciJ.v40.i5.10
A. V.
Vaganov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Sergei Mikhailovich
Drozdov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Sergey Mikhailovich
Zadonsky
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Iraida Fedorovna
Chelysheva
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Alexander Petrovich
Kosykh
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Garry Grantovich
Nersesov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Vladimir L'vovich
Yumashev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
aerospace vehicle
balancing flap
aerodynamic performance
numeric modeling
multiblock grids
parallel computing
Results of numeric modeling of three-dimensional flow around the configuration of the piloted orbital spaceship — the winged aerospace vehicle (ASV) proposed by the Central Hydrodynamic Institute [1−4] are presented and discussed in this paper. The flight vehicle with nondeflected control devices was examined in Ref. [4]. The effect of the deflection of the balancing flap on the flow field and the aerodynamic performance of the vehicle is studied here. The efficiency of the flap with its deflection from −5° to +10° is obtained. Computations were performed using the applied program package ARGOLA-2 for inviscid and thermally nonconductive gas within the range of incident flow Mach number from 1.1 to 16.5 and the angle of attack from zero to 45°. The effect of the real thermophysical properties of air on the aerodynamic performance of the winged ASV at hypersonic speed and the efficiency of the flap is estimated.
LIFT AND INDUCED DRAG OF A FINITE-SPAN WING IN A FLOW OF VISCOUS COMPRESSIBLE GAS AT SUBSONIC SPEEDS
535-551
10.1615/TsAGISciJ.v40.i5.20
Aleksander Sergeevich
Petrov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region
lift
wing-induced drag
compressible viscous gas
The method of transformation of the law of conservation of momentum for a continuum, applied by Zhukovsky [1] in the derivation of a profile lift theorem in an ideal incompressible fluid, is generalized for a spatial motion of a finite-span wing in a compressible viscous gas. As a result, we obtain an expression for the main vector of aerodynamic forces, which is the analog of the Zhukovsky theorem, but containing the side force and resistance force besides the lift. A correlation between the resistance force and the lift force is shown. An approximate analytical expression for the wing-induced drag in a viscous medium is obtained and the physical nature of its occurrence is studied. Limit as Re→∞, the Prandtl formula is for a wing-induced drag in an ideal fluid.
ON THE UNSTEADY FLUID FLOWS IN DOMAINS WITH CLOSED STREAMLINES
553-560
10.1615/TsAGISciJ.v40.i5.30
Anatoliy Vasil'evich
Zubtsov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovskystr., Zhukovsky, 140180, Moscow region, Russia
Aleksandr Marksovich
Gaifullin
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation
vorticity
flow
nonstationarity
self-similarity
viscosity
A non-steady-state flow in an area with a closed streamline has been considered for the case when vorticity w in the main approximation depends only on the stream function ψ and time t. From the Navier-Stokes equations an integral-differential equation was obtained for the function w(ψ, t). It is shown that this equation allows solutions which are self-similar by t. Specific examples of non-steady tasks are listed. The solution of these tasks are in line with the self-similar mode if t → ∞.
NOSE PARTS OF MINIMAL WAVE DRAG WITH THE FRONT FACE AND THE POWER-LAW GENEATRIX
561-569
10.1615/TsAGISciJ.v40.i5.40
Dmitry Sergeevich
Ivanyushkin
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovskystr., Zhukovsky, 140180, Moscow region, Russia
Sergey Alexandrovich
Takovitskii
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovskystr., Zhukovsky, 140180, Moscow region, Russia
noses
a wave drag
an optimization
a power low geneatrix
In this paper, we have considered the problem ofsearching for axisymmentrical nose parts of minimal wave drag. Optimization was realized in the class of bodies with a front face and power-law geneatrix. The radius of the front face and the power-law exponent are used as parameters of optimization. The nose parts, which were found on analytical solution of this task, were taken as initial bodies. Optimization was performed with the help of the method of cyclical coordinate-wise descent. The nose parts of the minimal wave drag have been obtained for lengthening λ = 1−8 at the Mach number M = 2 and for the range M = 1.5−4 at a fixed lengthening λ = 2. The obtained nose parts have been compared with the well-known optimal bodies on values of wave deag and geometrical parameters.
COMPARISON OFTHE RESULTS OF NUMERICAL CALCULATIONS BY THE METHOD BASED ON THE GODUNOV-KOLGAN-RODIONOV DIFFERENCE SCHEME WITH THE EXPERIMENTAL DATA FOR THE TRANSONIC FLOW AROUND RAE 2822 AIRFOIL
571-585
10.1615/TsAGISciJ.v40.i5.50
N. V.
Golovina
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
numerical simulation
Reynolds averaged Navier-Stokes equations
Coakley turbulence model
difference scheme of Godunov-Kolgan-Rodionov
analysis of accuracy of the computational method
viscous transonic flow over an airfoil
Results of the numerical calculation of the transonic viscous flow around the supercritical RAE 2822 airfoil are given. The numerical simulation was carried out on the basis of the solution of Reynolds-averaged Navier-Stokes equations enclosed using a Coakley two-parameter differential model of turbulence [1]. For the numerical solutions, a method based on the Godunov-Kolgan-Rodionov explicit difference scheme [2−4] and an EWT-TsAGI packet of application programs [5] was used. The computational studies of the airfoil were carried out to evaluate the accuracy of the numerical method. The coefficients of aerodynamic forces, pressure contours, distribution of the coefficient of friction drag, velocity profiles, and displacement thicknesses are given. The effects of the characteristic value of the velocity pulsations q, characteristic frequency of turbulent pulsations w, and the number of cells in the computational grid are discussed. The calculations have been carried out for several Mach numbers and are compared to classical experimental results [6] and calculation data [7−11].
ABOUT THE SECONDARY SEPARATION AT SUPERSONIC FLOW OVER A COMPRESSION RAMP
587-607
10.1615/TsAGISciJ.v40.i5.60
Vladimir Viktorovich
Shvedchenko
Central Aerohydrodynamic Institute (TsAGI) , Zhukovsky, Moscow region, Russia
compression ramp
separation
triple deck
supersonic flow
The numerical investigation of the separation at supersonic (M∞ = 5) flow over a compression ramp was carried out. The phenomenon of the secondary separation formation and development was considered in details. The separation stages were classified by a similarity parameter.
STUDY OF VISCOUS−INVISCID INTERACTION ON AN OSCILLATING MODEL OF AN AIRPLANE WITH A SWEPT WING
609-617
10.1615/TsAGISciJ.v40.i5.70
Ivan Vasilyevich
Kolin
Central Aerohydrodynamic Institute (TsAGI)
Vladimir Georgievich
Markov
Central Aerohydrodynamic Institute (TsAGI)
Viktor Konstantinovich
Svyatodukh
Central Aerohydrodynamic Institute (TsAGI)
Tamara Ivanovna
Trifonova
Central Aerohydrodynamic Institute (TsAGI)
Dmitry Valeryevich
Shukhovtsov
Central Aerohydrodynamic Institute (TsAGI)
swept wing
amplitude
frequency
unsteady separation
viscous-inviscid interaction
angle of attack
flow pattern
oscillation period
Strouhal number
Reynolds
Results are given of experimental studies (performed in a subsonic wind tunnel with an open working part) of flows over an airfoil of a model airplane with a swept wing oscillating with amplitudes Asub>α= 3 and 5° at a Strouhal number Shwz= 0.029 relative to setting angles of attack α0= 10 and 16° corresponding to single-valued (at α0 = 10°) and hysteretic (α0 = 16°) dependences of the static aerodynamic forces and moments on the angles of attack. It is shown that the extent of the development of unsteady separation on the oscillating wing is different at each moment in time during a single period of oscillations. Regimes of weak and moderate viscous-inviscid interactions and a regime of strong dynamic separation were investigated.
RESEARCH ON THERMAL DYNAMICS OF STRAIN-GAUGE BALANCE AND DEVELOPMENT OF METHODS FOR ITS TEMPERATURE ERROR REDUCTION
619-629
10.1615/TsAGISciJ.v40.i5.80
V. V.
Bogdanov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str, Zhukovsky, 140180, Moscow region, Russia
Valerii Semyonovich
Volobuyev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str, Zhukovsky, 140180, Moscow region, Russia
Anton Roaldovich
Gorbushin
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
multicomponent strain-gauge balance
wind tunnel
A study of thermodynamics of multicomponent strain-gauge balance was carried out and measures were proposed to reduce its temperature errors due to the nonstationary spatial gradients of temperature. The balance thermal dynamic model based on the method of electric thermal analogy was developed and experimentally tested. A method was proposed for taking into account the variations of the zero reading of strain-gauge balance during the experiment.
COMPOUND TRIANGULAR FINITE ELEMENT WITH CUBIC POLYNOMIAL FOR LATERAL PLATE BENDING
631-640
10.1615/TsAGISciJ.v40.i5.90
Julian Fedotovich
Yaremchuk
TUPOLEV, Academician Tupolev Embankment 17, Moscow, 105005, Russian
Federation
thin plate bending
triangular finite element
cross-element continuity
On the basis of a triangular compound-element of Clough-Tocher (CTE), the finite element with C1 smoothness1 (hereinafter ENP) was created, which geometrically coincides with the CTE but shows a nonlinear dependence in the normal derivative on the boundaries between the adjacent elements. In a specific case of linear dependence of the normal derivative along the boundaries, ENP and CTE are the same. The examples of a simply supported and clamped plate along the whole contour shows a noticeable improvement of the calculation is observed.