关键词: 斜爆震发动机;进气道;壁面温度;分离区;热边界层;数值模拟

Abstract: In order to study the effects of wall temperature on the flow field structure and flow parameters of oblique detonation engine inlet in laminar， transition and turbulent states， an oblique detonation engine inlet with curved compression section at Mach 10 was selected as the research object to conduct numerical simulation， and the changes of shock induced separation zone and thermal boundary layer near the inlet wall were deeply discussed. The numerical simulation results show that the wall cooling can restrain the phenomenon of relaminarization in the circular transition section of the inlet shoulder， and the relaminarization is the most serious under the condition of adiabatic wall. The increase of wall temperature is beneficial to delay the flow transition， and it also leads to the increase of separation area size and the moving forward of the main body of separation zone in transition and turbulent state. The transition in the inlet channel is separation induced transition. The transition position is mainly affected by the position of separation point. The overall performance is that the transition position gradually moves forward with the increase of wall temperature. With the increase of wall temperature， the thickness of thermal boundary layer on the top plate side of the inlet exit gradually thickens. In transition state， the thermal boundary layer thickness changes by up to 5%. The peak temperature on the top plate side of the inlet exit increases with the increase of wall temperature， and the peak position is gradually close to the wall. When the wall temperature is the same， the heat flux and thermal boundary layer thickness is smaller in the laminar flow state. In the transition and turbulent state， the thermal boundary layer on the top side of the inlet exit is thicker， which is about three times that of laminar flow， and the difference of thermal boundary layer thickness between transition and turbulent state can reach 2%.

Key words: Oblique detonation engine;Inlet;Wall temperature;Separation zone;Thermal boundary layer;Numerical simulation