Begell House Inc.
TsAGI Science Journal
TSAGI
1948-2590
45
7
2014
NOZZLE THRUST AUGMENTATION UNDER DIMENSIONAL CONSTRAINTS
571-579
10.1615/TsAGISciJ.2014012538
Sergey Alexandrovich
Takovitskii
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovskystr., Zhukovsky, 140180, Moscow region, Russia
supersonic nozzle
jet thrust
optimization
internal insert
The problem of designing axisymmetric supersonic nozzles is considered. In order to increase the jet thrust under dimensional constraints, the use an internal nozzle insert is proposed. The insert is located near the exit section outside the region of aerodynamic interference with the nozzle edge. The insert shape profiling and estimation of the thrust characteristics are performed by a direct optimization method. The research is performed within the framework of the Euler model for inviscid flow.
METHODOLOGY AND EXAMPLES OF NUMERICAL INVESTIGATIONS OF BODIES WITH DUCTS AT SUPERSONIC FLOW VELOCITIES
581-598
10.1615/TsAGISciJ.2014012837
Nina Vladimirovna
Voevodenko
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky St., Zhukovsky, Moscow Region, 140180, Russia
Anatoliy Aleksandrovich
Gubanov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky St., Zhukovsky, Moscow region, 140180, Russia
high-speed flying vehicle with air-breathing jet engine
numerical investigations
momentum theorem
The problem of computing the aerodynamic performance of high-speed flying vehicles (FVs) with airbreathing
jet engines is considered. An efficient, stable, rapid, robust, and informative computational instrument is required in investigations aimed at improving airframe design. A numerical method based on the hypersonic small-disturbance theory and the Godunov-Kolgan method is used in this study as the basic instrument in calculating the flow fields and total aerodynamic performance of a FV. In order to calculate the air inlet performance (mass flow rate coefficients, momentum components, etc.), the numerical results for the flow parameters at the entrance of the air inlet are used. The contribution of the engine air inlets to the total aerodynamic performance of the FV is determined by the momentum theorem. The results are compared with the experimental data and computational results using a Reynolds-averaged Navier-Stokes code. The performance of an axisymmetrical body with two air inlets is calculated.
INTERFERENCE CONCEPT OF AERODYNAMIC DESIGN OF EFFECTIVE HYPERSONIC CONFIGURATIONS
599-617
10.1615/TsAGISciJ.2014012528
Yury Ioasafovich
Lobanovsky
Irkut Corporation, Leningradskii Prospekt, 68, Moscow, 125315 Russia
hypersonic vehicle
wing
body
volume
waverider
lift
drag
lift-to-drag ratio
flow modes
An interference concept of aerodynamic design of hypersonic flying vehicles is presented, which makes it possible to develop some new configurations for efficient hypersonic flight. Wind tunnel tests of configurations designed on the basis of these principles with a volume coefficient typical for vehicles operating on a cryogenic fuel are performed at Mach numbers M = 7−10 and Reynolds numbers of the order of several million and provide the maximum lift-to-drag ratio (L/D)max = 5.7−5.6, which is 10−30% higher than that of currently available aerodynamic configurations. In contrast to known configurations, the lift-to-drag ratio of the new configurations does not decrease with increasing Mach
number. At M > 7 and full-scale Reynolds numbers, the lift-to-drag ratio of such configurations in cruising flight can reach (L/D)max ≈ 7. The aerodynamic characteristics of the proposed configurations at low and moderate supersonic speeds are similar to those of typical combinations of a body with a low-aspect-ratio wing.
INTERACTION OF A SUPERSONIC JET HEAVY LOADED BY PARTICLES WITH A SOLID BODY
619-638
10.1615/TsAGISciJ.2015013277
Galina Vasilievna
Molleson
Central Aerohydrodynamic Institute, Zhukovsky, Moscow region, Russia, 140180
Al'bert Leonidovich
Stasenko
Central Aerohydrodynamic Institute, Zhukovsky, Moscow region, Russia, 140180
gas-dynamic acceleration of microparticles
recovery coefficients of the velocity components
compressed layer
rotation of the bounced particles
chaotic particles and their diffusion
flux densities of mass
momentum and energy
The purpose of this work is to develop the physicomathematical model and numerical code for investigation of a monodisperse supersonic flow impinging on a solid axisymmetric body in the case of the large initial mass fraction of particulates. In such flows, a chaotic layer which can be described by the diffusion model arises on the surface of the body in flow. Several variants of the radial distribution of the particle concentration at the nozzle entrance are investigated (these distributions depend on the particulate kinetics in the mixing chamber and serve as a separate problem). The influence of particle
substance and dimensions on the flow gas thermodynamics is investigated for a large range of initial values of the particle mass density.
FUEL CONSUMPTION MINIMIZATION FOR AGRICULTURAL AIRCRAFT CONDUCTING SPRAYING
639-657
10.1615/TsAGISciJ.2015013290
Stanislav Nikolaevich
Suprunenko
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky 140180, Russia
Lam Thanh
Tang
Moscow Institute of Physics and Technology (MIPT), 9 Institutskiy per., Dolgoprudny, Moscow Region, 141700 Russia
agricultural aviation
aerial application
flight regime optimization
variational calculus
A problem of fuel consumption minimization for agricultural aircraft conducting spraying of chemicals in a horizontal flight is considered. The problem is formulated as an optimal control one to be solved by variational methods, with particular regard to the nonstationarity of aircraft full mass during flight and to the complexity of an engine's fuel consumption characteristics. A technique, proposed to determine the optimal solution, is based on an idea of making small improvements to the well-known quasi-stationary solution corresponding to an assumption of equality between the engine thrust and the aerodynamic drag. Illustrations of numerical computations fulfilled for the agricultural
airplane PZL M-15 (Soviet-Poland design) show that in the case of sufficiently intensive spray-mass expenditure the proposed optimal solution can noticeably raise the fuel saving.
EXPERIMENTAL INVESTIGATION OF THE AEROGASDYNAMICS OF A VECTORED-THRUST NOZZLE
659-667
10.1615/TsAGISciJ.2014012972
Gennadii Nikolaevich
Lavrukhin
Central Aerohydrodynamic Institute (TsAGI) 1, Zhukovsky str., Zhukovsky, 140180, Moscow region, Russia
Evgueny Borisovich
Skvortsov
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky St., Zhukovsky, Moscow Region, 140180, Russia
Vadim Alekseevich
Talyzin
Central Aerohydrodynamic Institute (TsAGI), 1 Zhukovsky Str., Zhukovsky 140180, Russia
turbofan
nozzle
thrust vectoring
subsonic flow
thrust losses
thrust vector angle
The results of the flow visualization and investigation of the aerogasdynamics characteristics of a turbofan engine nozzle with a thrust-vector control are presented. Some peculiarities of the flow and alteration of the nozzle characteristics with jet deflection are founded.