Performance evaluation of solid fuel scramjet under different inflow conditions

Biao Li; Zhi Jun Wei; Hong Wei Chi; Ning Fei Wang

doi:10.7673/j.issn.1006-2793.2014.04.007

Performance evaluation of solid fuel scramjet under different inflow conditions

Biao Li^*, Zhi Jun Wei, Hong Wei Chi, Ning Fei Wang

^*Corresponding author for this work

School of Aerospace Engineering

Beijing Institute of Technology

Research output: Contribution to journal › Article › peer-review

1 Citation (Scopus)

Abstract

Based on the characteristics of solid fuel scramjet, various components were designed preliminarily under the condition of free stream Ma=6 and flight altitude of 25 km. Numerical simulations were performed to analyze the performance variation law of each component and the whole engine under different inflow conditions. The results show that the flow capture ratio approximates 1 under the design point. When free stream Mach decreases to 4, the inlet becomes unstarted. With the free stream Mach increasing, the flame temperature increases and the combustion efficiency decreases gradually. The thrust is largest under the design point, and the specific impulse decreases with the increase of free stream Mach.

Original language	English
Pages (from-to)	469-474
Number of pages	6
Journal	Guti Huojian Jishu/Journal of Solid Rocket Technology
Volume	37
Issue number	4
DOIs	https://doi.org/10.7673/j.issn.1006-2793.2014.04.007
Publication status	Published - 1 Aug 2014

Keywords

Numerical simulation
Performance
Scramjet
Solid fuel

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title = "Performance evaluation of solid fuel scramjet under different inflow conditions",

abstract = "Based on the characteristics of solid fuel scramjet, various components were designed preliminarily under the condition of free stream Ma=6 and flight altitude of 25 km. Numerical simulations were performed to analyze the performance variation law of each component and the whole engine under different inflow conditions. The results show that the flow capture ratio approximates 1 under the design point. When free stream Mach decreases to 4, the inlet becomes unstarted. With the free stream Mach increasing, the flame temperature increases and the combustion efficiency decreases gradually. The thrust is largest under the design point, and the specific impulse decreases with the increase of free stream Mach.",

keywords = "Numerical simulation, Performance, Scramjet, Solid fuel",

author = "Biao Li and Wei, {Zhi Jun} and Chi, {Hong Wei} and Wang, {Ning Fei}",

year = "2014",

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doi = "10.7673/j.issn.1006-2793.2014.04.007",

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journal = "Guti Huojian Jishu/Journal of Solid Rocket Technology",

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TY - JOUR

T1 - Performance evaluation of solid fuel scramjet under different inflow conditions

AU - Li, Biao

AU - Wei, Zhi Jun

AU - Chi, Hong Wei

AU - Wang, Ning Fei

PY - 2014/8/1

Y1 - 2014/8/1

N2 - Based on the characteristics of solid fuel scramjet, various components were designed preliminarily under the condition of free stream Ma=6 and flight altitude of 25 km. Numerical simulations were performed to analyze the performance variation law of each component and the whole engine under different inflow conditions. The results show that the flow capture ratio approximates 1 under the design point. When free stream Mach decreases to 4, the inlet becomes unstarted. With the free stream Mach increasing, the flame temperature increases and the combustion efficiency decreases gradually. The thrust is largest under the design point, and the specific impulse decreases with the increase of free stream Mach.

AB - Based on the characteristics of solid fuel scramjet, various components were designed preliminarily under the condition of free stream Ma=6 and flight altitude of 25 km. Numerical simulations were performed to analyze the performance variation law of each component and the whole engine under different inflow conditions. The results show that the flow capture ratio approximates 1 under the design point. When free stream Mach decreases to 4, the inlet becomes unstarted. With the free stream Mach increasing, the flame temperature increases and the combustion efficiency decreases gradually. The thrust is largest under the design point, and the specific impulse decreases with the increase of free stream Mach.

KW - Numerical simulation

KW - Performance

KW - Scramjet

KW - Solid fuel

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U2 - 10.7673/j.issn.1006-2793.2014.04.007

DO - 10.7673/j.issn.1006-2793.2014.04.007

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AN - SCOPUS:84907935406

SN - 1006-2793

VL - 37

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EP - 474

JO - Guti Huojian Jishu/Journal of Solid Rocket Technology

JF - Guti Huojian Jishu/Journal of Solid Rocket Technology

IS - 4

ER -

Performance evaluation of solid fuel scramjet under different inflow conditions

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