摘要
为了研究攻角导致的来流定常/非定常变化对二元高超声速进气道性能的影响,在马赫3.85条件下,对一个设计马赫数为6.0的二元高超声速进气道进行了动态攻角变化的风洞实验。实验中,攻角在0°～8.2°连续变化,动态频率最大达到9.3Hz。实验研究表明:攻角在0°～8.2°连续变化过程中,进气道始终保持着起动状态;攻角增加使进气道出口增压比逐渐上升,流量系数、出口总压恢复系数和出口马赫数逐渐降低;在保持起动状态的攻角连续变化过程中,振荡的二元高超声速进气道其性能变化趋势与准稳态时相似,攻角的动态变化未对进气道性能产生显著影响。
In order to research the influence of dynamic angle-of-attack on the performance of 2-D hypersonic inlet,a rapid periodic dynamic angle-of-attack wind tunnel experiment is conducted at Mach 3.85.The angle-of-attack is 0°~8.2° and the frequency is up to 9.3 Hz.The results show that within the range of angle-of-attack the oscillating inlet works in starting mode.In the dynamic process of angle-of-attack,the performance parameters are influenced.The pressure rise of inlet will increase but the mass capture rate,total pressure recovery coefficient and the Mach number in throat of inlet tend to decrease with the rising of angle-of-attack.The performances of oscillating inlet with different frequencies are similar to the steady cases and there are no significantly changes throughout the oscillation.
出处
《推进技术》
EI
CAS
CSCD
北大核心
2012年第1期14-19,共6页
Journal of Propulsion Technology
关键词
高超声速进气道
攻角
风洞实验
非定常流动
Hypersonic inlet
Angle-of-attack
Wind tunnel experiment
Unsteady flow
