南京航空航天大学学报2011，Vol.43Issue(1)：13-17,5.
4种布局形式下超声速飞行器进气道气动特性实验对比
Mixed-Compression Supersonic Inlets Based on Four Air-Breathing Aircraft Configurations
谢文忠 1郭荣伟1
作者信息
- 1. 南京航空航天大学能源与动力学院,南京,210016
- 折叠
摘要
Abstract
An investigation is conducted in a wind tunnel to compare the aerodynamic characteristics of mixed-compression supersonic inlets based on four air-breathing aircraft configurations, including (1)axisymmetric inlet, (2) chin inlet, (3) twin-90° ventral 2D inlet, and (4) sweep-forward high-light "X"-type 2D inlet.Results indicate that: (1) The performances of these inlets have nearly the same tendencies versus Mach number, except that the mass flow ratio of sweep-forward high-light "X"-type 2D inlet decreases a little after Mach number reaching 1; (2) Both chin inlet and twin-90° ventral 2D inlet have better performances at the positive angle of attack and worse performance at negative angle of attack than the other two layouts, and the inlet performances of which decline slightly at 0-6° or -6-0°angle of attack, but decreases drastically when the angle of attack larger than ±6°.Also twin-90° ventral 2D inlet has the highest performance at the positive angle of attack; (3) The performance of three types decreases slightly at 0-4° yaw angle, except twin-90° ventral 2D inlet worse.关键词
超声速飞行器/轴对称进气道/下颔式进气道/双下侧二元进气道/"X"型倒置二元进气道Key words
supersonic crusing aircraft/ axisymmetric inlet/ chin inlet/ twin-90° ventral 2D inlet/sweep-forward high-light "X"-type 2D inlet分类
航空航天引用本文复制引用
谢文忠,郭荣伟..4种布局形式下超声速飞行器进气道气动特性实验对比[J].南京航空航天大学学报,2011,43(1):13-17,5.
