摘要
为提高高超声速翼身组合式飞行器的射程,研究了采用不同翼面变形模式时,飞行器在马赫数3~8内的气动特性和翼面效率。针对典型的轴对称翼身组合式外形,采用Navier-Stokes方程进行数值模拟,对伸缩、变后掠和二维折叠三种变形模式下的外形在超声速及高超声速来流条件下进行模拟,并对升阻比、翼面单位面积升阻比和操稳特性进行分析。结果表明:在超声速及高超声速范围内,变后掠变形模式在宽速域内升阻比提高明显,同时具备优良的翼面效率及操稳特性,其在马赫数3~8范围内具有最优的综合性能。研究成果能对高超声速翼身组合式变形飞行器布局设计提供参考,具有一定的指导意义。
Aiming at improving the range of wing-body combination aircraft at hypersonic flow conditions, the aerodynamic characteristics and wing efficiency of morphing tactical missile with different deformation modes at Mach number from 3 to 8 were studied. The Navier-Stokes equations were used to simulate the flow field , and the lift-to-drag ratio , wing efficiency , stability and controllability of different deformation modes as telescopic , variable sweep and two-dimensional folding were compared. Results show that under the condition of supersonic and hyper-sonic flow , the variable sweep wing mode improves the lift-to-drag ratio significantly , and at the same time , it has excellent wing efficiency and stability and controllability. The mode performs best at the Mach number from 3to 8. The conclusion can offer rome valuable guidance to the research and application of hypersonic morphing aircraft aerodynamic configuration.
作者
彭悟宇
杨涛
涂建秋
丰志伟
张斌
PENG Wuyu;YANG Tao;TU Jianqiu;FENG Zhiwei;ZHANG Bin(College of Aeronautics and Astronautics,National University of Defense Technology,Changsha 410073,China;China Academy of Launch Vehicle Technology,Beijing 100076,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2018年第3期15-21,共7页
Journal of National University of Defense Technology
基金
国防科技大学科研计划资助项目(JC-13-04)
关键词
变形飞行器
高超声速
翼面变形模式
升阻比
操稳比
morphing aircraft
hypersonic
wing deformation modes
lift-to-drag ratio
stability and controllability
