复杂变截面进气道的一种设计方法  

Unique design method of subsonic inlet with complex cross-sectional shape

作　　者：周慧晨[1] 谭慧俊[1] 李湘萍 

机构地区：[1]南京航空航天大学内流研究中心,南京210016 [2]南京模拟技术研究所,南京210016

出　　处：《航空动力学报》2009年第6期1357-1363,共7页Journal of Aerospace Power

基　　金：航空科学基金(05C52022)

摘　　要：提出了一种基于曲率控制的截面形状生成与过渡技术,可实现进气道任意进口截面形状向出口圆截面的过渡,以此为基础编制了进气道设计程序,能快速且可视地完成各种具有复杂进口截面形状、复杂弯曲形式的进气道设计,并可对进气道通道的各种特征参数进行监控,为下一步复杂变截面进气道的参数化研究奠定了基础.作为初步应用,还完成了多种进口形式的进气道型面设计,并以类X-47狭缝式进气道为例进行了详细介绍.A cross-sectional shape generating method for subsonic inlet design was proposed according to curvature regulation. This unique method can realize the transition of an arbitrary entrance shape to the exit circular shape easily and smoothly. Utilizing this method, an inlet design procedure was programmed, which could accomplish the surface composition of subsonic inlet with complex cross-sectional shape and complex bending style quickly and graphically. As a preliminary application, several diffusers with different entrance shape were generated and especially the design procedure of a slot-shaped inlet like that of X-47 vehicle was described in detail.

关 键 词：复杂变截面进气道 狭缝式进气道 设计方法 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]