Design and Performance Analysis of Hypersonic Forebody Based on Conic Section

被引：0
|
作者：
Yuan H.-C. [1 ]
Chen W.-F. [1 ]
Liu J. [1 ]
Hua Z.-X. [1 ]
机构：
[1] Nanjing University of Aeronautics and Astronautics, Jiangsu Province Key Laboratory of Aerospace Power Systems, Nanjing
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2017年 / 38卷 / 08期
关键词：
Conic section; Forebody configuration; Lateral overflow; Lift-to-drag ratio; Mass flow ratio;
D O I：
10.13675/j.cnki.tjjs.2017.08.005
中图分类号：
学科分类号：
摘要：
In order to investigate the effects of different configuration of hypersonic forebody on the performance of inlet, the hypersonic forebody was designed based on conic section under the same external compression angles and compression ramp length conditions and analyzed through three dimension numerical simulation. The effects of four hypersonic forebody cross section parameters including width ratio, shape parameter, angle parameter and order of horizontal half width control curve were analyzed. The numerical simulation results indicated that these four parameters affected the performance of the inlet according to the influence of the lateral pressure gradient along the forebody. The increase of the width ratio, shape parameter and order of horizontal half width control curve and decrease of angle parameter would reduce the lateral pressure gradient and lateral overflow and increase the mass flow ratio of the inlet. In this paper, the change of these four parameters improved the inlet mass flow ratio by 25.1%, 13.7%, 20.3% and 12.2%, respectively. © 2017, Editorial Department of Journal of Propulsion Technology. All right reserved.
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页码：1717 / 1725
页数：8
相关论文
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