Access the full text.
Sign up today, get DeepDyve free for 14 days.
(2007)
Processing and Visualization of Physical Experiment Data Using the Origin Package, Astrakhan Institute for Advanced Qualification and Retraining
(2019)
Integrated approach to solving the problem of a high-speed flow around a body in a pulsed aerodynamic installation and checking the consistency of the results obtained
(1964)
Slezinger, Aeromechanical Measurements (Methods and Devices)
(2016)
Numerical investigation of pseudoshock formation in a channel
P. Bulat, O. Zasuhin, V. .Uskov (2012)
On classification of flow regimes in a channel with sudden expansionThermophysics and Aeromechanics, 19
(2009)
Snegirev, High-Performance Computing in Technical Physics. Numerical Modeling of Turbulent Flows: Textbook
E. Dimarzio, C. Guttman (1969)
Separation by FlowMacromolecules, 3
(2014)
Gas-Dynamic Installations of Short-Term Action. Part 1. Installations for Scientific Research
(2019)
Actual problems of modern continuum mechanics and celestial mechanics -2019
(2016)
Experimental investigation of the peculiarities of supersonic flow around the bodies of different shapes, Intelligent energy systems
IG Gudich, VT Zhukov, KV Manukovsky (2016)
Numerical simulation and visualization of combustion flows in a high-velocity combustion chamberScientific Visualization, 8
A. Ishchenko, E. Maslov, N. Skibina, V. Faraponov (2021)
Complex Investigation of Nonstationary Flow with Shock Waves in the Working Path of a Hypersonic Ramjet EngineJournal of Engineering Physics and Thermophysics, 94
NP Skibina (2019)
Mathematical modeling of gas-dynamic processes in a pulsed aerodynamic facility and the numerical calculation of flow parameters in the test chamberComputational Technologies, 24
(2016)
Manukovsky, Numerical simulation and visualization of combustion flows in a high-velocity combustion chamber
(2017)
Influence of backpressure on the flow in the diffuser of a supersonic air inlet
IG Gudich (2016)
104Scientific Visualization, 8
Надежда Скибина (2019)
Mathematical modeling of gas-dynamic processes in a pulsed aerodynamic facility and the numerical calculation of flow parameters in the test chamberВычислительные технологии
The paper describes a study of pressure distribution along the wall of an axisymmetric channel with a straight step. A supersonic gas flow formed inside the channel when an external flow with Mach numbers M = 5 and M = 6 moves around an axisymmetric model with internal duct is considered. A supersonic aerodynamic wind tunnel of a short-term action is used for experiments. The results of measuring the pressure along the channel wall in the flow around the model under study are presented. The data of aerodynamic tests are compared with the results of numerical calculations, and the resulting pressure distributions are compared. It has been established that the nonmonotonic nature of a change in pressure along the wall is caused by the shock waves, which accompany the supersonic gas flow in the channel.
Thermophysics and Aeromechanics – Springer Journals
Published: Jan 1, 2022
Keywords: aerodynamic tests; pressure recording; axisymmetric channel; shock waves
Read and print from thousands of top scholarly journals.
Already have an account? Log in
Bookmark this article. You can see your Bookmarks on your DeepDyve Library.
To save an article, log in first, or sign up for a DeepDyve account if you don’t already have one.
Copy and paste the desired citation format or use the link below to download a file formatted for EndNote
Access the full text.
Sign up today, get DeepDyve free for 14 days.
All DeepDyve websites use cookies to improve your online experience. They were placed on your computer when you launched this website. You can change your cookie settings through your browser.