Performance analysis of a strut-aided hypersonic scramjet by full-scale IDDES modeling

被引：21

作者：

Yao, Wei ^{[1
,2
]}

Liu, Hang ^{[1
,2
]}

Xue, Lianjie ^{[1
,2
]}

Xiao, Yabing ^{[1
,2
]}

机构：

[1] Chinese Acad Sci, Inst Mech, Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China

[2] Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China

来源：

AEROSPACE SCIENCE AND TECHNOLOGY | 2021年 / 117卷

基金：

国家自然科学基金重大研究计划;

关键词：

Hypersonic combustion; Hydrogen; Improved Delayed Detached Eddy; Simulation (IDDES); Dynamic zone flamelet model; Scramjet; LARGE-EDDY SIMULATION; CONDITIONAL MOMENT CLOSURE; DISSIPATION RATE; JET; COMBUSTION; INJECTION; DIFFUSION; FLAMES; LES;

D O I：

10.1016/j.ast.2021.106941

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The uninstalled performance of a full-scale scramjet operating over Mach 7 to 10 and altitudes of 28 to 40 km was numerically analyzed by using high-fidelity Improved Delayed Detached Eddy Simulation (IDDES) with 125.10 million cells and Dynamic Zone Flamelet model (DZFM) with 21,294 flamelet zones. The inviscid thrust can be well correlated with dynamic pressure in the form of a gaussian function, whereas the viscous drag increases almost linearly with dynamic pressure. For the examined scramjet, net thrust is achieved for the low dynamic pressure range below 37 kPa and the high range above 55 kPa. The rule of mixed is burnt is observed, and the final combustion efficiencies vary from 66% to 82%. The upstream propagation of combustion occurs for most of the cases in the current strut-based combustor, and unstart occurs for the case of Mach 7 at 30 km. (C) 2021 Elsevier Masson SAS. All rights reserved.

引用

页数：14