摘要
采用模块化方法设计了一组具有“钻石背”弹翼的风洞实验模型,进行了六分量测力实验,实验马赫数范围为Ma=0.4~0.8,攻角范围为-2°~12°,俯仰控制舵偏角为-5°,实验结果表明:“钻石背”弹翼能提供较大的升力,具有“钻石背”弹翼的飞行器升阻比可达5以上,有很强的滑翔增程能力,适用于无动力制导炸弹的滑翔增程;攻角〉6°时,升力随攻角变化曲线的当地斜率迅速降低,应按最大升阻比选择滑翔飞行的攻角。
A series of wind tunnel experiment models with various Diamond Back wings were designed with a modularized method, and 6-component measuring experiments were conducted to study the aerodynamic characteristics of the Diamond Back wings under the coditions of Ma = 0.4-0. 8, a = - 2°- 12° and δ2 = - 5°. The experimental results indicate that the Diamond Back wing is suitable for gliding extended range of unpowered guided bomb unit based on high lifting force, CL/CD≥5 and high gliding extended range ability; the local slope of CL- α curve reduces rapidly under the condition of α〉6°; the attack angle of gliding flight should be selected according to maximum CL/CD.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2007年第7期893-896,共4页
Acta Armamentarii
关键词
流体力学
气动布局
气动特性
风洞实验
“钻石背”弹翼
制导炸弹
fluid dynamics
aerodynamic configuration
aerodynamic characteristic
wind tunnel experiment
Diamond Back wing
guided bomb