摘要
为解决高超声速飞行器在低/跨/超声速时气动特性不佳的问题,实现水平起降、跨速域飞行的目标,设计了一种宽速域变构型高超声速飞行器。采用数值计算的方法对飞行器的低速、超声速和高超声速气动特性和典型流场进行了研究分析,得到了升力系数、阻力系数和升阻比随攻角和马赫数的变化规律。结果表明,飞行器在低速和高超声速时的气动特性较好,最大升阻比分别为15.37和4.08,低速时连接翼提供了高升力,高超声速时乘波效果显著;超声速时,阻力系数和升阻比受马赫数影响较大,最大升阻比为4.8。数值计算的结果表明飞行器在全速域范围内气动特性较好,在保证高超声速良好气动特性的前提下,提升了低/跨/超声速性能。
In order to solve the poor aerodynamic characteristics of a hypersonic vehicle at low speed,transonic speed and supersonic speed,realize the goal of horizontal take-off,landing and cross-range flight.A wide-ranged morphing hypersonic vehicle has been designed.In this paper,the numerical computing methods have been used to investigate its aerodynamic characteristics and typical flow field at three mentioned speeds.The variation regularity of lift ratio,drag ratio and lift-drag ratio under different angles of attack and Mach numbers have been found.It has been shown that the aerodynamic characteristics of vehicle are good at low speed and hypersonic speed and the maximum value of lift-to-drag ratio is 15.37 and 4.08,respectively.High lift has been acquired by joinedwing at low speed and the effect of wave-rider is outstanding at hypersonic speed.Drag ratio and lift-drag ratio is heavily affected by the Mach number and the maximum value of lift-to-drag ratio is 4.8 at supersonic speed.The obtained result shows that its aerodynamic characteristics is good at full speed range and the performance at low/transonic/supersonic speed has been improved on the premise of ensuring good aerodynamic characteristics at hypersonic speed.
作者
张登成
罗浩
张艳华
郑无计
ZHANG Dengcheng;LUO Hao;ZHANG Yanhua;ZHENG Wuji(Institute of Aeronautics Engineering,Air Force Engineering University,Xi’an 710038,China)
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2019年第1期128-134,共7页
Journal of Solid Rocket Technology
关键词
高超声速
变构型飞行器
气动特性
流场分析
hypersonic
morphing vehicle
aerodynamic characteristics
flow field analysis
