Experimental investigation on drag and heat flux reduction in supersonic/hypersonic flows: A survey

被引：108

作者：

Wang, Zhen-guo ^{[1
]}

Sun, Xi-wan ^{[1
]}

Huang, Wei ^{[1
]}

Li, Shi-bin ^{[1
]}

Yan, Li ^{[1
]}

机构：

[1] Natl Univ Def Technol, Sci & Technol Scramjet Lab, Changsha 410073, Hunan, Peoples R China

来源：

ACTA ASTRONAUTICA | 2016年 / 129卷

基金：

中国国家自然科学基金;

关键词：

Drag and heat reduction; Forward-facing cavity; Opposing jet; Aerospike; Energy deposition; Supersonic/hypersonic flows; MULTIOBJECTIVE DESIGN OPTIMIZATION; COMBINATIONAL OPPOSING JET; THERMAL PROTECTION SYSTEM; FORWARD-FACING CAVITY; HIGH-SPEED; BLUNT-BODY; COUNTERFLOWING JET; HYPERSONIC FLOW; SUPERSONIC-FLOW; ABLATION ONSET;

D O I：

10.1016/j.actaastro.2016.09.004

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The drag and heat reduction problem of hypersonic vehicles has always attracted the attention worldwide, and the experimental test approach is the basis of theoretical analysis and numerical simulation. In the current study, research progress of experimental investigations on drag and heat reduction are summarized by several kinds of mechanism, namely the forward-facing cavity, the opposing jet, the aerospike, the energy deposition and their combinational configurations, and the combinational configurations include the combinational opposing jet and forward-facing cavity concept and the combinational opposing jet and aerospike concept. The geometric models and flow conditions are emphasized, especially for the basic principle for the drag and heat flux reduction of each device. The measurement results of aerodynamic and aerothermodynamic are compared and analyzed as well, which can be a reference for assessing the accuracy of numerical results. (C) 2016 IAA. Published by Elsevier Ltd. All rights reserved.

引用

页码：95 / 110

页数：16

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