|Table of Contents|

Investigation of thrust/drag property of scramjet(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2014年06期
Page:
41-45
Research Field:
研究与设计
Publishing date:

Info

Title:
Investigation of thrust/drag property of scramjet
Author(s):
ZHAO Hong-liang;  ZHANG Meng-zheng
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
scramjet;  thrust characteristic;  research method;  measurement technology
PACS:
V434-34
DOI:
-
Abstract:
Thrust and drag are the most important characteristic parameters of scramjet, which consists of inlet, combustor and nozzle. The research status of the component-level and the overall thrust/drag characteristics are reviewed in this paper. The research methods and measurement technology for the thrust/drag characteristics of scramjet are introduced. Some suggestions are proposed for the future study: investigating the accurate free-jet test measurement technology, investigating the impact of the flow field uniformity on scramjet performance, and developing the high-precision simulation platform.

References:

[1]IGARASHI Y, MITANI T, KODEAR M, et al. Comparative studies on scramjet engine drag by experiments and numerical analysis, AIAA98-1512[R]. USA: AIAA, 1998.
[2]ODAM J, PAULL A. Comparison of experimental thrust measurements with theoretical values for a scramjet engine[C]// AIAA International Space Planes and Hypersonic Systems and Technologies. [S.l.]: AIAA, 2003: 1-10.
[3]DENNER BW. CFD prediction of inlet spill drag increments, AIAA 98-3566[R]. USA: AIAA, 1998.
[4]CONNERS T R, HOWE D C. Supersonic inlet shaping for dramatic reductions in drag and sonic boom strength, AIAA 2006-30[R]. USA: AIAA, 2006.
[5]金志光, 张堃元. 典型二元高超声速进气道与侧压式进气道的性能比较[J]. 航空动力学报, 2008, 23(9):1553- 1560.
[6]卫永斌, 张元, 骆晓臣. 二元高超声速进气道内部阻力特性分析与研究[J]. 空气动力学报, 2010, 28(1): 104-108.
[7]卫永斌, 张元. 三维侧压式高超声速进气道阻力特性分析[J]. 航空动力学报, 2009, 24(7): 1594-1600.
[8] 常军涛, 鲍文, 崔涛, 等. 抽吸对高超声速进气道抗反压能力的影响[J]. 航空动力学报, 2008, 23(3): 505-509.
[9]LUO Shi-bin, HUANG Wei. Drag force chara- cteristic of a typical dual-mode scramjet com- bustor[C]// 2010 2nd International Conference on Computer Engineering and Technology. [S.l.]: [s.n.], 2010(5): 255-259.
[10]王兰, 邢建文, 郑忠华, 等. 超燃冲压发动机内流性能的一维评估[J]. 推进技术, 2008, 29(6): 641-645.
[11]吴先宇, 李小山, 丁猛, 等. 超燃冲压发动机燃烧室构型对燃烧室性能影响[J]. 2008, 29(3): 300- 305.
[12]苏义,刘卫东. 支板阻力特性实验[J]. 航空动力学报,2009, 24(12): 2643-2648.
[13]潘余, 丁猛. 超燃冲压发动机凹腔火焰稳定器阻力分析[J]. 推进技术, 2009, 30(5): 518-522.
[14]GENIN F, MENON S. LES of supersonic combustion of hydrocarbon spray in a scramjet, AIAA 2004-4132[R]. USA: AIAA, 2004.
[15]黄伟, 柳军, 罗世彬, 等. 凹腔布局对高超声速飞行器气动-推进性能影响[J]. 固体火箭技术, 2010, 33(2): 138- 141.
[16]潘余, 丁猛, 梁剑寒, 等. 超燃冲压发动机多凹腔串联燃烧室阻力研究[J]. 航空学报, 2010, 31(1): 70-75.
[17]HSU K Y. Experimental study of cavity-strut combustion in supersonic flow, AIAA 2007- 5394[R]. USA: AIAA, 2007.
[18]CHANG Xin-yu, GU Hong-bin, CHEN Li-hong. Thrust and drag of a scramjet model with different combustor geometries, AIAA 2005-3315[R]. USA: AIAA, 2005.
[19]陈立红, 顾洪斌, 张新宇. 支板凹腔一体化超燃冲压发动机实验研究[J].工程热物理学报, 2007, 28(4): 717- 719.
[20]MARATHE A G, THIAGARAJAN V. Effect of geometric parameters on the performance of single expansion ramp nozzle, AIAA 2005-4429[R]. USA: AIAA, 2005.
[21]MEISS J H, MEINKE M. Numerical investigation to enhance the thrust vector of a scramjet nozzle, AIAA 2011-2346[R]. USA: AIAA, 2011.
[22]COCHRAN R B. Hypersonic nozzle/afterbody performance at low mach numbers, AD-A216 223[R]. USA: Air Force Inst. of Tech., 1989.
[23]LU Xin, YUE Lian-jie. Design of scramjet nozzle employing streamline tracing technique, AIAA 2009-7248 [R]. USA: AIAA, 2009.
[24]全志斌, 徐惊雷, 莫建伟. 单边膨胀喷管膨胀型面的非线性缩短设计[J]. 推进技术, 2012, 33(6): 951-955.
[25]莫建伟, 徐惊雷, 全志斌. 截短单边膨胀喷管的试验和数值模拟[J]. 推进技术, 2012, 33(6): 940 -945.
[26]FERGUSON F, DHANASAR M. A model for the design and analysis of thrust optimized scramjets, AIAA 2009- 7337[R]. USA: AIAA, 2009.
[27]KLICHE D, MUNDT C. Combustor modelling for multidisciplinary analysis and evaluation of supersonic combustion ramjets, AIAA 2009-7282[R]. USA: AIAA, 2009.
[28]王兰, 邢建文, 郑忠华, 等. 超燃冲压发动机内流性能的一维评估[J]. 推进技术, 2008, 29(6): 641-645.
[29]任鑫, 罗春钦, 董建明, 等. 超燃冲压发动机性能的准二维计算方法[J].推进技术, 2013, 34(4):457-462.
[30]贺伟, 于时恩, 李宏斌. 高超声速一体化飞行器推阻特性测量研究[J]. 试验流体力学, 2010, 4(2): 65-68.
[31]LOCKWOOD M K, PETLEY D H, HUNT J L, et al. Airbreathing hypersonic vehicle design and analysis methods, AIAA 96-0381[R]. USA: AIAA, 1996.
[32]郑日恒. 法国冲压发动机研究进展[J]. 航天制造技术,2006, 4(2): 6-10.
[33]马洪强, 高贺, 毕志献. 高超声速飞行器相关的摩擦阻力直接测量技术[J]. 试验流体力学, 2011, (25)4: 83-88.

Memo

Memo:
-
Last Update: 1900-01-01