- 44 - www.ivypub.org/EEA Electrical Engineering and Automation December 2013, Volume 2, Issue 4, PP.44-51 Design and Numerical Simulation of Submerged S-shaped Inlet Duct Sangcao Ge # , Rong Cui National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100191, China #Email: [email protected]Abstract Submerged S-shaped inlet applied on Blended Wing Body aircraft would ingest fuselage boundary layer, as the boundary layer cannot resist adverse pressure gradient in duct and may cause flow separation, thus leading to the total pressure loss and outlet distortion, which is the core problem of S-shaped inlet. Wall curvature of S-shaped duct can cause local adverse pressure gradient, while wall pressure gradient is important reasons for the development of the boundary layer and loss. In order to control and optimize the wall pressure distribution of the S-shaped inlet and investigate the relationship between the pressure distribution and aerodynamic performance of the S-shaped inlet, the paper developed a two-dimensional geometry model which can build the association of wall pressure distribution and wall curvature allocation; then three-dimensional model was built. By numerical simulation, the wall pressure distribution and aerodynamic performance of S-shaped inlet duct were analyzed in this paper at the condition of uniform intake and boundary layer ingestion. The results showed that the wall pressure distribution trend at different longitudinal locations remains approximately, and at the condition of uniform intake the wall pressure distribution of three- dimensional model is similar to the two-dimensional model, so the feasibility of the design method is proved; and further the ingested boundary layer causes large scale of flow separation at the inner wall, the total pressure recovery decreases and the outlet distortion index increases. Keywords: S-shaped Inlet; Wall Curvature; Wall Pressure Distribution; Boundary Layer Ingestion (BLI); Pressure Recovery; Distortion 埋入式 S 形进气道内通道设计及数值模拟 格桑草,崔容 北京航空航天大学航空发动机气动热力重点实验室,北京 100191 摘 要:应用于翼身融合布局飞机的埋入式 S 形进气道由于摄入的机身边界层在 S 形通道中难以抵抗逆压梯度而会导致 流动分离,这是造成 S 形进气道流动损失和出口畸变的核心问题。 S 形管道壁面曲率会导致壁面当地的不利压力梯度,管 道壁面压力梯度是影响壁面边界层发展和管道损失产生的重要原因。为优化控制 S 形进气道壁面压力分布并研究其与 S 形进气道气动性能的关系,首先从进气道壁面压力分布与壁面曲率关系出发,建立二维壁面参数化模型,然后进行三维 模型设计并进行数值模拟,分析均匀进气与畸变进气即边界层摄入两类进气工况下, S 形进气道壁面压力分布的规律及其 气动性能。结果表明:在不同纵向截面位置,S 形进气道内外壁面压力分布趋势相互近似,且在均匀进气时二维模型与三 维模型壁面压力分布相似,验证了设计方法的可行性;畸变进气时,摄入的边界层在 S 形管道内壁面处发生较大尺度分 离,使进气道总压恢复系数下降而出口畸变指数增大。 关键词:S 形进气道;壁面曲率;壁面压力分布;边界层摄入;总压恢复系数;畸变 基金资助:受国家自然科学青年基金 * 支持资助(批准号:10902008)
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Design and numerical simulation of submerged s shaped inlet duct
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- 44 -
www.ivypub.org/EEA
Electrical Engineering and Automation December 2013, Volume 2, Issue 4, PP.44-51
Design and Numerical Simulation of Submerged
S-shaped Inlet Duct Sangcao Ge #, Rong Cui
National Key Laboratory on Aero-Engines, Beijing University of Aeronautics and Astronautics, Beijing 100191, China