|Table of Contents|

Design of 2-D curved compression hypersonic inlet with wide Mach number range(PDF)

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

Issue:
2015年01期
Page:
43-49
Research Field:
研究与设计
Publishing date:

Info

Title:
Design of 2-D curved compression hypersonic inlet with wide Mach number range
Author(s):
NAN Xiang-Jun
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
2-D inlet;  curved compression;  wide operation range;  bleeding on top
PACS:
V434-34
DOI:
-
Abstract:
Design method of 2-D curved compression with controlled pressure rise law is used to design a 2-D hypersonic inlet with wide operation range of Ma 2-7 at design point of Ma 6 for RBCC engine. A sweep forward side wall is used to reduce internal contraction ratio of inlet, and air bleeding slots are placed on top wall to expand operation range of inlet below Ma 4. Three dimensional numerical simulation is conducted in the range of Ma 1.5-7. The numerical results show that the new-type 2-D inlet with curved compression has less shock waves, good flow field structure and excellent performance in the range of Ma 4-7. With air bleeding on top wall, it can operate well in the range of Ma 1.5-4, and the air bleeding mass ratio is below 15%. Analysis turns out the curved compression inlet has high performance above Ma 4, but low mass capture capability below Ma 4.

References:

[1]SIEBENHAAR A, BULMAM M J, BONNAR D K. Strutjet rocket based combined cycle engine[R]. USA: NASA, 1999.
[2]TERSUO H, KATSUHIRO I, SHIGERU S，et al. Recent progress in scramjet/ combined cycle engines at JAXA, kakuda space propulsion center，AIAA 2006-555[R]. USA: AIAA, 2006.
[3]SUSUMU H, DOYLE K，Numerical analysis and optimi- zation of two-dimensional hypersonic inlets, AIAA 2004- 856[R]，USA: AIAA, 2004.
[4]梁德旺. 二元高超声速进气道设计体系及优化[C]//2005年高超声速进气道技术交流（研讨）会论文集. 南京: [s.n.], 2005.

[5]徐旭，蔡国飙. 超燃冲压发动机二维进气道优化设计方法研究[J]. 推进技术, 2001, 22(6): 468-472.

[6]张晓嘉, 梁德旺, 李博, 等. 典型二元高超声速进气道设计方法研究[J]. 航空动力学报，22(8): 1290-1296.
[7]VOLAND R T. ROCK K E, HUEBNER L D, et al. Hyper- X engine design and ground test program, AIAA-98-1532[R]. USA: AIAA, 1998.
[8]JOSEPH M H, JAMES S M, RICHARD C M. The X-51A scramjet engine flight demonstration program, AIAA 2008-2540[R]. USA: AIAA, 2008.
[9]潘瑾, 张堃元, 金志光. 弯曲激波压缩型面的设计及数值分析[J]. 推进技术, 2008, 29(4):438-442.
[10]张林, 张堃元, 王磊, 等. 基于壁面马赫数梯度的高超声速弯曲激波二维进气道数值研究[J].航空动力学报, 2013, 28(4): 752-758.
[11]王磊，张堃元，向有志，等. 高超声速二元弯曲激波压缩面反设计方法的参数化研究[J]. 南京航空航天大学学报, 2013, 45(4): 441-446.
[12]南向军，张堃元，金志光. 基于反正切曲线压升规律设计高超内收缩进气道[J]. 航空动力学报, 2011, 26(11): 2571-2577.
[13]杜炜强, 吴宝元. 高超声速进气道优化设计初探[J]. 火箭推进, 2007, 33(6): 17-21.
[14]张蒙正, 李斌, 路媛媛. 矩形流道RBCC 动力系统推阻特性之思考[J]. 火箭推进, 2014, 40(3): 1-6.
[15]贺武生. 超燃冲压发动机研究综述[J]. 火箭推进, 2005, 31(1): 29-32.
[16]侯早, 王福民, 旷武岳. 冲压发动机超声速进气道研究进展[J]. 火箭推进, 2008, 34(5): 31-34.

Memo

Memo:
-
Last Update: 1900-01-01