一种二元定几何混压式超声速进气道流场控制概念研究

翁小侪; 郭荣伟

一种二元定几何混压式超声速进气道流场控制概念研究

翁小侪^1,2,
郭荣伟¹

1.
南京航空航天大学能源与动力学院, 南京 210016
2.
中国人民解放军 94710部队, 江苏无锡 214141

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出版历程
- 收稿日期: 2011-11-04
- 刊出日期: 2012-11-28

Study of novel flow control concept for fix-geometry two-dimensional mix-compression supersonic inlet

WENG Xiao-chai^1,2,
GUO Rong-wei¹

1.
College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
Unit 94710, the Chinese People's Liberation Army, Wuxi Jiangsu 214141, China

摘要

摘要: 针对二元定几何混压式超声速进气道低马赫数时流量系数低加速性能差的问题,提出了一种新的泄流槽流场控制概念,并通过数值仿真,揭示了泄流槽控制激波结构机理及其主要几何参数对进气道性能的影响规律.研究结果表明:采用该流场控制方案可通过泄流槽入口处的波系结构使进气道在低于设计马赫数时的出口总压恢复系数和流量系数相对于原型方案均得到明显提高,而在设计点关闭泄流槽后进气道的性能与原型进气道基本相当,这对改善冲压发动机在低马赫数转级后的加速性能是有利的.
- 航空、航天推进系统 /
- 冲压发动机 /
- 二元超声速进气道 /
- 流场控制 /
- 泄流槽
Abstract: A novel flow control concept was presented to improve the performance of fix-geometry two-dimensional mix-compression supersonic inlet when the free stream Mach number was lower than the cruising Mach number.This concept is placing a special bypass-slot at the front-end of the second ramp,which can change the configuration of the shock wave system to enhance the performance of the inlet.The numerical results indicate that when the free stream Mach number is smaller than the cruising Mach number,compared with the initial inlet,the flow control can raise the total pressure recovery coefficient and mass flow ratio significantly.Whereas the performance of the inlet declines little at the design point with the bypass-slot shut.In conclusion,the flow control concept is beneficial to the ramjet engine under the speeding up condition.
- aerospace propulsion system /
- ramjet engine /
- two-dimensional supersonic inlet /
- flow control /
- bypass-slot

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参考文献(15)

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