The weak shock waves impact on the flow in the boundary layer of the sweep flat plate at Mach number 2 is studied experimentally. The model was installed at a zero angle of attack. Shock waves in the oncoming flow were generated by a two-dimensional roughness on the side wall of the wind tunnel test section. The data were obtained with a two-dimensional roughness on the wall of the wind tunnel and with a smooth wall at sweep angles (35 and 40 degrees) of the leading edge of the flat blunt plate. The measurements were carried out with a constant temperature anemometer.
|Журнал||Journal of Physics: Conference Series|
|Состояние||Опубликовано - 6 дек. 2019|
|Событие||16th All-Russian Seminar with International Participation on Dynamics of Multiphase Media, DMM 2019 - Novosibirsk, Российская Федерация|
Продолжительность: 30 сент. 2019 → 5 окт. 2019