等压力梯度曲面压缩系统性能参数化分析  

Parametric Investigation of Constant Pressure Gradient Curved Compression System

作　　者：潘瑾[1] 金峰[2] 张堃元[2] 

机构地区：[1]南京航空航天大学金城学院,南京210016 [2]南京航空航天大学能源与动力学院,南京210016

出　　处：《重庆理工大学学报（自然科学）》2013年第8期26-31,40,共7页Journal of Chongqing University of Technology：Natural Science

基　　金：国家自然科学基金重大研究计划项目(90916029)

摘　　要：根据激波和膨胀波理论,设计了等压力梯度曲面压缩系统并进行试验验证。数值分析了来流条件和曲面设计参数对等压力梯度曲面压缩系统性能的影响。通过研究发现:初始压缩角对等压力梯度曲面压缩系统的性能影响较大。给出了等压力梯度曲面及其弯曲激波型线预估公式,并由试验验证了激波型线的最大相对误差为4.8%。According to the shock wave and expansion wave theory, a constant pressure gradient curved compression system is designed and proven by wind tunnel test. The influence about inflow condition and design parameters on the property of constant pressure gradient curved compression sys- tem is investigated by numerical analysis. The result shows the initial compression angle is the most important influence parameter for constant pressure gradient curved compression system. Predictor for-mulas for the profile lines of constant pressure gradient curved compression system and curved shock wave is given. The maximum relative error between shapes for curve shock wave of predictor formulas and experiment is 4.8 percent.

关 键 词：超声速进气道 曲面压缩 等压力梯度 弯曲激波 数值分析 

分 类 号：V235[航空宇航科学与技术—航空宇航推进理论与工程]