Aerodynamic configuration integration design of hypersonic cruise aircraft with inward-turning inlets

作     者：Jifei WANG Jinsheng CAI Chuanzhen LIU Yanhui DUAN Yaojie YU 

作者机构：School of Aeronautics Northwestern Polytechnical University Aerodynamics Theory and Application Institute China Academy of Aerospace Aerodynamics Computational Aerodynamics Institute China Aerodynamics Research and Development Center 

基　　金：supported by the ‘‘111" Project of China (No. B17037) 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2017年第30卷第4期

页      码：1349-1362页

摘      要：In this work, a novel airframe/propulsion integration design method of the wing-body configuration for hypersonic cruise aircraft is proposed, where the configuration is integrated with inward-turning inlets. With the help of this method, the major design concern of balancing the aerodynamic performance against the requirements for efficient propulsion can be well addressed. A novel geometric parametrically modelling method based on a combination of patched class and shape transition（CST） and COONs surface is proposed to represent the configuration, especially a complex configuration with an irregular inlet lip shape. The modelling method enlarges the design space of components on the premise of guaranteeing the configuration integrity via special constraints imposed on the interface across adjacent surfaces. A basic flow inside a cone shaped by a dual-inflection-point generatrix is optimized to generate the inward-turning inlet with improvements of both compression efficiency and flow uniformity. The performance improvement mechanism of this basic flow is the compression velocity variation induced by the variation of the generatrix slope along the flow path. At the design point, numerical simulation results show that the lift-to-drag ratio of the configuration is as high as 5.2 and the inlet works well with a high level of compression efficiency and flow uniformity. The design result also has a good performance on off-design conditions. The achievement of all the design targets turns out that the integration design method proposed in this paper is efficient and practical.

主 题 词：Aerodynamic configurations Hypersonic Integration design Inward turning inlet Numerical simulation 

学科分类：080103[080103] 08[工学] 080104[080104] 0801[工学-力学类] 

核心收录：

D　O　I：10.1016/j.cja.2017.05.002

馆 藏 号：203254894...