高马赫数低噪声风洞层流喷管设计与性能评估  

Design and Performance Evaluation for High Mach Number Low Noise Wind Tunnel Nozzle

作　　者：高亮杰[1,2] 钱战森[1,2] 王璐[1,2] 王彤[1,2] 

机构地区：[1]中国航空工业空气动力研究院气动发展部,辽宁沈阳110034 [2]高速高雷诺数气动力航空科技重点实验室,辽宁沈阳110034

出　　处：《航空科学技术》2016年第8期68-78,共11页Aeronautical Science & Technology

基　　金：航空科学基金(2013ZD26004)~~

摘　　要：层流喷管作为高马赫数低噪声风洞的核心部件,对风洞性能起决定性作用。本文概述了高马赫数低噪声风洞层流喷管的2项关键技术,即喉道前边界层抽吸控制与亚跨超段衔接型线匹配设计技术研究现状,研究了基于喉道上游边界层抽吸的喷管亚跨超段一体化设计方法和基于数值方法的喷管转捩预测技术,可指导高马赫数低噪声风洞的研制。The purpose of laminar nozzles, which is one of the key components of high Mach number low noise wind tunnels, is to delay boundary layer transition process. Two key design methods play a decisive role, include boundary layer suction before the nozzle throat and profiles integrated design and matching. This paper presents the laminar nozzle research development, which focuses on integrated design methods based on boundary layer suction and transition prediction based on numerical methods, to provide support for ground test equipment construction.

关 键 词：高马赫数层流喷管 边界层抽吸 逆向特征线法 稳定性因子 层流脉动能 转捩预测 

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]