矩形截面高超声速变几何进气道研究  

Designing methodology and flow characteristic of hypersonic variable geometry inlet with rectangular section

作　　者：袁化成[1] 郭荣伟[1] 

机构地区：[1]南京航空航天大学内流研究中心,江苏南京210016

出　　处：《空气动力学学报》2013年第2期192-197,共6页Acta Aerodynamica Sinica

基　　金：南京航空航天大学基本科研业务费专项科研项目(NS2010054)

摘　　要：为了改善宽马赫数范围工作的进气道性能,对矩形截面高超声速变几何进气道进行了研究,提出并设计了一种包括唇口开启、唇口后退等几何动作的变几何进气道设计方案。据此在马赫数Ma=4.0～6.5范围内设计了矩形截面高超声速变几何进气道,采用数值仿真方法对其气动性能开展了研究,并与定几何进气道性能进行了对比。研究结果表明:设计马赫数及高于设计马赫数条件下,变几何进气道与定几何进气道的性能基本相同。低于设计马赫数时,变几何进气道的性能明显优于定几何进气道。In this paper, based on the fixed hypersonic inlet with rectangular section, a new concept of variable geometry hypersonic inlet that the tip can turn and move back off to increase the mass capture ratio is presented, and operating in a large Mach number range from 4 to 6.5. The flow in the hypersonic inlet was analyzed with numerical analyzer, and the inlet performance comparisons were made between the variable ge- ometry hypersonic inlet and fixed inlet at different Mach number of inflow. The results indicated that the performance of the variable geometry inlet as much as fixed one under design Mach number, and the perform- ance of the variable geometry inlet was better than fixed inlet under non design point. All of that indicate that the variable geometry hypersonic inlet was satisfying.

关 键 词：矩形截面 高超声速进气道 变几何 设计方法 数值模拟 

分 类 号：V211.48[航空宇航科学与技术—航空宇航推进理论与工程]