Variable leading-edge cone method for waverider design  

作　　者：Zhihao LI Chongwen JIANG Shuyao HU Chun-Hian LEE 

机构地区：[1]School of Aeronautic Science and Engineering,Beihang University,Beijing 100191,China [2]Shenzhen Institute of Beihang University,Shenzhen 518000,China

出　　处：《Chinese Journal of Aeronautics》2025年第3期262-279,共18页中国航空学报(英文版)

基　　金：supported by grants from the National Natural Science Foundation of China(No.U20B2006);the Guangdong Basic and Applied Basic Research Foundation(No.2022A1515110145);Young Elite Scientists Sponsorship Program by China Association for Science and Technology(No.2022QNRC001).

摘　　要：The optimization of the waverider is constrained by the reversely designed leading edge and the constant shock angle distribution. This paper proposes a design method called the variable Leading-Edge Cone (vLEC) method to address these limitations. In the vLEC method, the waverider is directly designed from the preassigned leading edge and the variable shock angle distribution based on the Leading-Edge Cone (LEC) concept. Since the vLEC method is an approximate method, two test waveriders are designed and evaluated using numerical simulations to validate the shock design accuracy and the effectiveness of the vLEC method. The results show that the shocks of the test waveriders coincide well with the preassigned positions. Furthermore, four specifically designed application cases are conducted to analyze the performance benefits of the vLEC waveriders. The results of these cases indicate that, due to their variable shock angle distributions, the vLEC waveriders exhibit higher lift-to-drag ratios and better longitudinal static stability than conventional waveriders. Additionally, the vLEC waveriders demonstrate superior volumetric capacities near the symmetry plane, albeit with a minor decrease in volumetric efficiency.

关 键 词：Hypersonic vehicles Waverider design methods Leading-edge cone method Variable shock angles Direct design method 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]