Numerical investigation of air flow in a supersonic wind tunnel

In the framework of TsAGI's supersonic wind tunnel modernization program aimed at improving flow quality and extending the range of test regimes it was required to design and numerically validate a new test section and a set of shaped nozzles: two flat nozzles with flow Mach number at nozzle ex...

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Bibliographic Details
Published in:Journal of physics. Conference series 2017-11, Vol.891 (1), p.12043
Main Authors: Drozdov, S M, Rtishcheva, A S
Format: Article
Language:English
Subjects:
Air flow
CAD
Circuits
Computer aided design
Diffusers
Flow simulation
Flux density
Heat flux
High temperature
Mach number
Modernization
Nozzles
Perturbation
Physics
Static pressure
Supersonic wind tunnels
Three dimensional flow
Two dimensional flow
Uniform flow
Viscosity ratio
Wind tunnel walls
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Summary:In the framework of TsAGI's supersonic wind tunnel modernization program aimed at improving flow quality and extending the range of test regimes it was required to design and numerically validate a new test section and a set of shaped nozzles: two flat nozzles with flow Mach number at nozzle exit M=4 and M=5 and two axisymmetric nozzles with M=5 and M=6. Geometric configuration of the nozzles, the test section (an Eiffel chamber) and the diffuser was chosen according to the results of preliminary calculations of two-dimensional air flow in the wind tunnel circuit. The most important part of the work are three-dimensional flow simulation results obtained using ANSYS Fluent software. The following flow properties were investigated: Mach number, total and static pressure, total and static temperature and turbulent viscosity ratio distribution, heat flux density at wind tunnel walls (for high-temperature flow regimes). It is demonstrated that flow perturbations emerging from the junction of the nozzle with the test section and spreading down the test section behind the boundaries of characteristic rhomb's reverse wedge are nearly impossible to eliminate. Therefore, in order to perform tests under most uniform flow conditions, the model's center of rotation and optical window axis should be placed as close to the center of the characteristic rhomb as possible. The obtained results became part of scientific and technical basis of supersonic wind tunnel design process and were applied to a generalized class of similar wind tunnels.
ISSN:1742-6588
1742-6596
DOI:10.1088/1742-6596/891/1/012043