Design and experimental study of a practical Osculating Inward Cone Waverider Inlet

作     者：He Xuzhao Zhou Zheng Qin Si Wei Feng Le Jialing 

作者机构：Science and Technology on Scramjet Laboratory Hypervelocity Aerodynamics Institute of CARDC 

基　　金：supported by the National Natural Science Foundation of China (Nos. 51376192 and 91216303) 

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

年 卷 期：2016年第29卷第6期

页      码：1582-1590页

摘      要：A design method based on tip to tail streamline tracing and osculating inward cone methods is discussed for designing the integrated Osculating Inward Cone Waverider Inlet（OICWI）. A practical geometrical constrained experimental model of OICWI is designed based on the validated design method. It has a total contraction ratio of 4.61 and inner contraction ratio is 2.0. Wind-tunnel tests have been conducted for the OICWI model at free stream Mach number（Ma） of 4.0, 3.5 and 3.0 respectively. The experimental results show that the OICWI has high flow capture ratio and compression abilities. It can self-start at Ma= 3.5 and 4.0 and its flow capture ratio is 0.73 at Ma= 4.0, and Angle of Attack（AOA） 0°. The research results show that the OICWI has advantages of inward cone waverider and streamline tracing inlet. Present OICWI is a novel approach for waverider inlet integration studies and it will promote the use of waverider inlet integration configuration in the studies of airbreathing hypersonic vehicles.

主 题 词：Inlet Integration design Inward turning cone Waverider Wind tunnel experiment 

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.2016.09.007

馆 藏 号：203210197...