Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
48
8
2017
NEW TYPE OF PULSED THERMAL ACTUATOR
683-698
10.1615/TsAGISciJ.2018026652
Aleksandr Vladimirovich
Voevodin
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Anton Andreevich
Kornyakov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Aleksander Sergeevich
Petrov
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region
D. A.
Petrov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Georgiy Grigoryevich
Soudakov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky Str. 1, Zhukovsky 140180, Russia
actuator
plasma
pulse
mathematical model
experiment
calculation
ejector
Methods to control the gas flow around an aircraft by pulsed thermal actuators of various types are considered. The operation principles and flight modes in which they can be effectively used are discussed. It is argued that the known types of plasma actuators can be effective only at low flight velocities of unmanned aerial vehicles. To extend the range of flight velocities, a new type of actuator
is considered, namely, a pulsed thermal actuator. The calculations show that this actuator has a serious disadvantage, which is active zone overheating at high pulse repetition frequencies. Several types of pulsed thermal actuators are proposed and studied. One of which (an open-ended actuator) is designed for operation at high repetition frequencies and transonic flow velocities. Its potential
capability of operation at frequencies on the order of 1 kHz is demonstrated, which is sufficient to control the majority of aerodynamic processes at high subsonic velocities. It is shown that the use of such actuators in applications with tangential jet flows is much less effective from the energy
point of view compared to boundary layer suction. A new type of actuator (an ejector-type pulsed thermal actuator) is proposed for the suction regime. This actuator provides simultaneous suction of the boundary layer from the upper surface of the wing and gas ejection in the trailing edge region. The suction velocity ensured by the operating model of the actuator is determined in experiments by
hot wire anemometry.
CONTROL OF VORTEX FLOW OVER A MANEUVERABLE AIRCRAFT MODEL USING NOSE FLAPS AT LARGE ANGLES OF ATTACK
699-709
10.1615/TsAGISciJ.2018026350
Konstantin Anatolievich
Osipov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Moscow Region, Russia
ribbed front part
model of maneuverable aircraft
nose flaps
sweep angle
large angles of attack
aerodynamic coefficients
vortices
loss of stability
vortex breakdown
asymmetry
Navier–Stokes equations
numerical methods
The results of a numerical study of the effect of nose flaps on the longitudinal and lateral aerodynamic characteristics of a maneuverable aircraft model are presented. Analysis of the numerical aerodynamic characteristics and visualization of the flow fields showed that changing the location
of the nose flaps along the fuselage may increase the range of linear dependence of the lift coefficient on the angle of attack by Δα ≈ 4° starting from α = 16° as well as increase the lift coefficient and aerodynamic efficiency by ΔK ≈ 0.8 at α = 20°. An increase in the sweep angle due to the extension of the nose flaps located on the front part of the model also leads to an increase in the lift coefficient
at large angles of attack and increases the range of the linear dependence of the lift coefficient on the angle of attack by Δα = 8° starting from α = 16° and aerodynamic efficiency by ΔK ≈ 1 at α = 20°. A one-sided extension of the nose flap to generate additional increments of the roll and yaw moments is considered.
MIXING LAYER STRUCTURE OF A JET IN A WIND TUNNEL WITH AN OPEN TEST SECTION
711-722
10.1615/TsAGISciJ.2018026655
N. I.
Batura
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Valery Viktorovich
Vozhdaev
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Gadzhi Gadzhimagomaevich
Gadzhimagomedov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Igor Ivanovich
Lipatov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russia; Moscow Institute of Physics and Technology (MIPT), 9 Institutskiy Per.,
Dolgoprudny, Moscow Region, 141701, Russian Federation
wind tunnel with an open test section
particle image velocimetry
mixing layer
computational fluid dynamics
turbulence model
The mixing layer structure of a jet in a closed-circuit wind tunnel with an open test section is studied by advanced methods of numerical modeling and experimental measurements. The experimental results are compared with the numerical solutions to the Navier–Stokes equations and boundary
layer theory for a free plane-parallel turbulent incompressible jet.
THREE-DIMENSIONAL AFTERBODY DRAG WITH NOZZLE JET
723-750
10.1615/TsAGISciJ.2018026680
Gennadii Nikolaevich
Lavrukhin
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russia
Vadim Alekseevich
Talyzin
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky 140180, Russia
afterbody
axisymmetric and flat nozzles
external drag
sub- and transonic flows
jet
interference
This paper summarizes the results of investigation in Russia and abroad within the scope of external drag of afterbodies with nozzles (axisymmetric, flat, nonsymmetric) at subsonic and transonic Mach numbers. Fundamental phenomena of separation and nonseparation flow pattern are considered, including the effect of positive interference of the jet with sub- and transonic external flow. The influence of the geometric parameters of the afterbody with a jet nozzle on their drag is shown; the criteria for the flow around it to be attached and the conditions for ensuring a minimum external drag are formulated.
NONCONTACT MEASUREMENTS OF WING BOX DEFORMATION DURING STRENGTH TESTS BY VIDEOGRAMMETRY METHOD
751-760
10.1615/TsAGISciJ.2018026351
Vladimir Petrovich
Kulesh
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky, 140180, Russia
K. A.
Kuruliuk
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
Mikhail Aleksandrovich
Fedotov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
noncontact measurements
videogrammetry
strength tests
structural failure
deformations fields
Deformation measurements of a wing box prototype of medium-range civil aircraft were performed by the noncontact optical videogrammetry method. The prototype was made of a polymer composite material. Investigations were carried out during residual strength tests of the wing box. Loading
was applied with a step of 10% of ultimate load in flight mode until failure. Distributed deformation fields of bending and twisting of the wing box were obtained for each loading step. The measurement error of normal deviations of surface points did not exceed 0.8 mm. It was shown that maximum bending of the wing tip section reached 290 mm just before destruction.
TASKS OF THE MODAL TEST AND REPRODUCTION OF FORCES BY MEANS OF ELECTROMECHANICAL SIMULATION
761-771
10.1615/TsAGISciJ.2018026703
Vsevolod Igorevich
Smyslov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky str. 1, Zhukovsky, 140180 Russia
modal experiment
reproduction of forces
electromechanical simulation
tasks
The main problems of ground-based experiments aimed at identifying modal characteristics and reproduction of force impacts are discussed. The latter has a lot of similarity in terms of the hardware and software used. The issues concerning boundary conditions, influence of excitation means on aircraft construction, and aerodynamic forces that arise in preparation for aircraft ground-based experiments are discussed, and several solutions to these issues are suggested in this article.
BEAM STIFFNESSES OF A COMPOSITE WING WITH ANISOTROPIC SKIN
773-787
10.1615/TsAGISciJ.2018026632
E. I.
Kryuchkov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky,
Moscow Region, 140180, Russian Federation
aircraft wing
composite anisotropic structure
beam stiffnesses
Equations for the definition of beam stiffnesses, positions of neutral axes, and rotation centers at bending and torsion, stresses, and deformations of a composite wing with an anisotropic skin are obtained based on the classical beam theory. A comparison of the results obtained from the analytical solutions and the results obtained from the finite-element computations is performed.
CONTENTS, VOLUME 48, 2017
789-797
10.1615/TsAGISciJ.v48.i8.80