Adiabatic wall temperature and heat transfer coefficient influenced by separated supersonic flow

Alexander Leontiev,Sergey Popovich,Yurii Vinogradov,Mark Strongin,D Markovich,D Zaitsev,A Semenov

doi:10.1051/epjconf/201715900030

Alexander Leontiev, Sergey Popovich + Show 5 more

Open Access

https://doi.org/10.1051/epjconf/201715900030

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Journal: EPJ web of conferences	Publication Date: Jan 1, 2017
Citations: 11	License type: cc-by

Affiliation: Lomonosov Moscow State University

Abstract

Investigations of supersonic air flow around plane surface behind a rib perpendicular to the flow direction are performed. Research was carried out for free stream Mach number 2.25 and turbulent flow regime - Rex >2·107 . Rib height was varied in range from 2 to 8 mm while boundary layer thickness at the nozzle exit section was about 6 mm. As a result adiabatic wall temperature and heat transfer coefficient are obtained for flow around plane surface behind a rib incontrast with the flow around plane surface without any disturbances.

Highlights

One of the major problems in high speed vehicles engineering is the accuracy of experimental data obtained in supersonic wind tunnels while its extrapolation to the real flight conditions
One of the main problems in the equation (1) is definition of adiabatic wall temperature Taw [3, 4]. In engineering applications it is defined by means of temperature recovery factor r, total temperature T0, Mach number M and the ratio of specific heats γ:
The physical meaning of temperature recovery factor r is that it shows a part of the flow kinetic energy that is transformed to the heat on the wall [1,2,3,4]

Summary

Introduction

One of the major problems in high speed vehicles engineering is the accuracy of experimental data obtained in supersonic wind tunnels while its extrapolation to the real flight conditions. One of the main problems in the equation (1) is definition of adiabatic wall temperature Taw [3, 4] In engineering applications it is defined by means of temperature recovery factor r, total temperature T0, Mach number M and the ratio of specific heats γ: Taw T0 r M 1 1 M2 (2). The physical meaning of temperature recovery factor r is that it shows a part of the flow kinetic energy that is transformed to the heat on the wall [1,2,3,4] It is defined by means of adiabatic wall temperature Taw, total temperature T0 and static temperature T:

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