Characteristics of the AT-303 hypersonic wind tunnel. Part 1. Velocity Fields

Kharitonov, A. M.; Звегинцев, В. И.; Vasenev, L. G.; Kuraeva, A. D.; Nalivaichenko, D. G.; Новиков, А. В.; Paikova, M. A.; Chirkashenko, V. F.; Shakhmatova, Nadezhda V.; Shpak, S. I.

doi:10.1134/s1531869906010011

Cited by 8 publications

(3 citation statements)

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“…The volumetric compression ratio (CR) between the CT and LT (defined as the volume of the LT and CT combined divided by the volume of the compression tube, (V LT + V CT )/V LT ) and initial temperature in the LT are set so that the test slug is at the stagnation temperature of the desired flight condition. In using the adiabatic compression of a preheated gas, the proposed facility is similar to the ITAM AT-303 tunnel [11], but with two distinct differences which simplify operation: the device performing the compression (i.e. the piston) only operates in the unheated section of the facility, and pressure regulation devices are not required to control the piston trajectory.…”

Section: Facility Descriptionmentioning

confidence: 98%

Adiabatic-compression preheated Ludwieg tube for the realistic simulation of hypersonic flows

Chung¹,

Laurence²

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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We describe a novel hypersonic facility to reproduce the high stagnation pressures and temperatures necessary for the accurate simulation of hypersonic flows in the range Mach 5-7, while providing test times sufficiently long to study unsteady flow effects. The facility uses a preheated Ludwieg tube together with a piston-compression stage to generate reservoir temperatures difficult to achieve with electrical heating alone, but also avoiding the introduction of vitiation contaminants. The absence of shocks in the generating flow is expected to lead to increased flow quality while also providing longer test times compared to shock-driven facilities. The operational concept is described and a condition for optimal operation is defined based on minimizing the dimensions of the heated section for a given set of desired flow conditions. A simple theoretical treatment shows that this condition constrains the ratio of the nozzle exit and Ludwieg tube diameters, assuming proper simulation of flight conditions. A method-of-characteristics solver is used to determine the constrained facility parameters more accurately. Modeling of the unsteady adiabatic compression cycle is performed with quasi-one-dimensional Euler computations, and various configurations are explored to minimize the pressure oscillations generated during compression.

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Section: Facility Descriptionmentioning

confidence: 98%

Adiabatic-compression preheated Ludwieg tube for the realistic simulation of hypersonic flows

Chung¹,

Laurence²

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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“…The pressure sensor produced a uniform signal suitable for subsequent processing. Further processing of the recorded signals was performed by a standard procedure used for áô-303 [10].…”

Section: Pressure Distribution Over the Surfacementioning

confidence: 99%

Aerothermodynamics of expert ballistic vehicle at hypersonic speeds

Kharitonov

Adamov

Chirkashenko

et al. 2012

Progress in Flight Physics

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The European EXPErimental Re-entry Test bed (EXPERT) vehicle is intended for studying various basic phenomena, such as the boundary-layer transition on blunted bodies, real gas e¨ects during shock wave/boundary layer interaction, and e¨ect of surface catalycity. Another task is to develop methods for recalculating the results of windtunnel experiments to §ight conditions. The EXPERT program implies large-scale pre §ight research, in particular, various calculations with the use of advanced numerical methods, experimental studies of the models in various wind tunnels, and comparative analysis of data obtained for possible extrapolation of data to in- §ight conditions. The experimental studies are performed in various aerodynamic centers of Europe and Russia under contracts with ESA-ESTEC. In particular, extensive experiments are performed at the Von Karman Institute for Fluid Dynamics (VKI, Belgium) and also at the DLR aerospace center in Germany. At ITAM SB RAS, the experimental studies of the EXPERT model characteristic were performed under ISTC Projects 2109, 3151, and 3550, in the T-313 supersonic wind tunnel and AT-303 hypersonic wind tunnel.

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“…2 and 3, respectively. The experimental technique was described in [10]. The computational grid had 1000 nodes in the axial direction and 40 nodes over the nozzle radius.…”

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confidence: 99%

Numerical design of multimodal axisymmetric hypersonic nozzles for wind tunnels

Aul’chenko

Galkin

Звегинцев

et al. 2010

J Appl Mech Tech Phy

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A method for design of hypersonic nozzles for wind tunnels is developed and implemented on the basis of solving direct problems with various models of the medium and numerical methods of integration of gas-flow equations. Multimodal nozzles for operation in Mach number ranges M out = 8-14 and M out = 14-20 satisfying specified requirements are designed.Introduction. It is known that a good quality of the wind-tunnel flow is ensured by using carefully designed nozzles accelerating the gas flow to a specified velocity. Almost all existing wind tunnels use unimodal nozzles designed for certain operation conditions. As such nozzles are manufactured with specialized equipment providing precision accuracy and are extremely expensive, they are limited in number; therefore, the number of wind-tunnel operation regimes is also limited.The AT-303 hypersonic wind tunnel based at the Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Division of the Russian Academy of Sciences is designed for operation in wide ranges of the Mach and Reynolds numbers. Therefore, the issue of using multimodal nozzles that can form flows with different parameters with the minimum changes in the nozzle structure has been discussed all the time after wind-tunnel commissioning. The present paper describes the sequence of actions and methods used in numerical design of multimodal nozzles for the AT-303 hypersonic wind tunnel.Multimodal Nozzle Variants. A preliminary analysis of possible variants of the multimodal nozzle was based on the model of an ideal perfect gas. The most effective option in this model for a uniform flow with the output Mach number M out is the use of a three-parameter family W (γ, M out , G) of supersonic contours with a plane sonic line at the input and a uniform characteristic at the output (γ is the ratio of specific heats, M out is the output Mach number, and G is the ratio of the flow rate through the streamline used to construct the nozzle to the flow rate of the nozzle with a corner point). If the ambient pressure does not exceed the pressure at the nozzle exit (output pressure), the operation domain of such nozzles is shaped as a diamond, which can be obtained by means of mirror reflection of the uniform characteristic with respect to the abscissa axis and with respect to the vertical straight line passing through the end point of the nozzle. Obviously, each nozzle of this kind corresponds to one operation mode. The procedure of constructing the family of the contours W (γ, M out , G) by the method of characteristics was described in [1].Variant No. 1. Using the family of the contours W (γ, M out , G) for two modes M 1 and M 2 , we can design a nozzle consisting of a fixed part adjacent to the throat section and a replaceable part adjacent to this fixed part on the right. In this paper, we consider only a bimodal nozzle, but further construction is also applicable to multimodal nozzles as well. The nozzle is constructed as follows:

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Characteristics of the AT-303 hypersonic wind tunnel. Part 1. Velocity Fields

Cited by 8 publications

References 0 publications

Adiabatic-compression preheated Ludwieg tube for the realistic simulation of hypersonic flows

Adiabatic-compression preheated Ludwieg tube for the realistic simulation of hypersonic flows

Aerothermodynamics of expert ballistic vehicle at hypersonic speeds

Numerical design of multimodal axisymmetric hypersonic nozzles for wind tunnels

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