Aerodynamic cooling for supersonic wake flow behind a backward-facing step

The results of an experimental study of the effect of reducing the adiabatic wall temperature (aerodynamic cooling) for a case of separated supersonic flow behind a backward-facing step are presented. The study was conducted on unsteady-state regime during the launching a wind tunnel before reaching the equilibrium thermal state. The parameters of thermal gas dynamics were compared with the results obtained for the case of continuous flow around the smooth wall. The free-stream Mach number was 2.2, the Reynolds number along the length of the dynamic boundary layer was at least 20 million at the nozzle exit section. The height of the step ranged from 8 to 12 mm. The graphs of the wall temperature, stagnation flow temperature, adiabatic wall temperature, the total and static pressure, the heat flux, the distribution of the temperature recovery coefficient and the relative Stanton number along the length of the model are presented. The studies were carried out in the joint inter-university laboratory of MSU-BMSTU "Thermal Gas Dynamics" on the experimental base of the Research Institute of Mechanics of Lomono-sov Moscow State University.

aerodynamic cooling, adiabatic wall temperature, temperature recovery coefficient, heat transfer coefficient, supersonic flow, temperature stratification

Volume 20, issue 1, 2019 year

Аэродинамическое охлаждение стенки при течении сверхзвукового потока в следе за обратным уступом

Представлены результаты экспериментального исследования эффекта снижения адиабатной температуры стенки (аэродинамического охлаждения) при отрывном течении сверхзвукового потока за уступом. Исследование проводилось на нестационарном режиме в процессе запуска аэродинамической установки до выхода на равновесный тепловой режим. Параметры термогазодинамики сравнивались с результатами, полученным при безотрывном обтекании гладкой стенки. Число Маха набегающего потока составило 2.2, критерий Рейнольдса по длине динамического пограничного слоя – не менее 2·10^7 на срезе сопла. Высота уступа варьировалась от 8 до 12 мм. Представлены графики изменения в процессе эксперимента температуры стенки и потока, полного и статического давления, теплового потока, а также распределения по длине модели коэффициента восстановления температуры и относительного числа Стантона. Исследования выполнены в совместной межвузовской лаборатории МГУ-МГТУ «Термогазодинамика» на экспериментальной базе НИИ механики МГУ.

аэродинамическое охлаждение, адиабатная температура стенки, коэффициент восстановления температуры, коэффициент теплоотдачи, сверхзвуковой поток, температурная стратификация

Volume 20, issue 1, 2019 year

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