基于反正切曲线压升规律设计高超内收缩进气道  

Design of hypersonic inward turning inlets with basic flowfield using arc tangent curve law of pressure rise

作　　者：南向军[1] 张堃元[1] 金志光[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2011年第11期2571-2577,共7页Journal of Aerospace Power

基　　金：国家自然科学基金(90916029)

摘　　要：采用反正切曲线压升规律设计了轴对称基准流场,该压升规律初始部分压缩较缓,可产生较弱的前缘激波,末尾部分压缩较缓,可产生较小的内收缩比,中间部分压缩量较大,主要对气流压缩.对该压升规律的3个系数进行了参数化研究,得到各系数对流场压缩效率,压缩量,以及重要几何参数的影响规律.基于该基准流场设计了圆形进口内收缩进气道,并进行了无黏及黏性数值研究.结果表明:采用该压升规律可以有效减小进气道前缘激波强度,提高压缩效率,同时具有较小的参考内收缩比,进气道在设计点和非设计点均具有良好的流量捕获特性和较高的压缩效率.Numerical simulation was performed to study the performance of axisymmetric basic flowfield with arc tangent curve law of pressure rise, helping to weaken the leading shock wave and reduce the reference internal contraction ratio. This curve has three parameters, whose effects on the performance parameters such as total pressure recovery, static pressure ratio, contraction ratio and internal contraction ratio were studied. Finally, a circular inward turning inlet with the basic flowfield was designed and numerically simulated to get the flow characteristics and total performance. The result shows this inlet has weak leading shock wave and small internal contraction ratio, as well as high mass capture ratio and compression efficiency both on design point and off design point.

关 键 词：高超进气道 内收缩进气道 基准流场 压升规律 数值模拟 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]