Hot-wire measurements of the evolution of total temperature and mass flow pulsations in supersonic boundary layer on flat plate with coating permeability

A. D. Kosinov, N. V. Semionov, Yu G. Yermolaev, G. L. Kolosov, A. A. Yatskikh, V. L. Kocharin

Research output: Chapter in Book/Report/Conference proceedingConference contributionResearchpeer-review

6 Citations (Scopus)

Abstract

An experimental study of supersonic boundary layer on a flat plate with coating permeability at two Mach numbers 2 and 2.5 was carried out. The flow disturbances were measured by a constant-temperature anemometer (CTA), operating in the scanning regime. The procedure for calibrating a constant-temperature anemometer has been performed. It was shown that the coefficients of sensitivity to pulsations of mass flow rate and stagnation temperature are practically independent of the Mach number of the oncoming flow. In experiments on a flat plate with porosity, the positions of the laminar-turbulent transition were determined. The obtained experimental data can be used in calculations and numerical prediction of a laminar-turbulent transition in a supersonic boundary layer.

Original languageEnglish
Title of host publication19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
Editors Fomin
PublisherAmerican Institute of Physics Inc.
Number of pages5
Volume2027
ISBN (Electronic)9780735417472
DOIs
Publication statusPublished - 2 Nov 2018
Event19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 - Akademgorodok, Novosibirsk, Russian Federation
Duration: 13 Aug 201819 Aug 2018

Publication series

NameAIP Conference Proceedings
PublisherAMER INST PHYSICS
Volume2027
ISSN (Print)0094-243X

Conference

Conference19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
CountryRussian Federation
CityAkademgorodok, Novosibirsk
Period13.08.201819.08.2018

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