摘要
新一代超/高超音速飞行器要求具有高空空气动力机动能力、长航程能力,使飞行器具有细长弹身和带进气道等外形特征。牛顿碰撞类方法在高超声速钝头体外形的气动特性预测中,有较成熟的应用。本文将其推广应用于新一代超/高超声速带进气道飞行器外形的气动力特性预测。计算了大量新一代超/高超飞行器带进气道外形,气动力系数和力矩系数的结果与试验结果吻合都较好,证明本文方法适用于新一代超/高超带进气道飞行器的气动力特性快速计算,并具有计算速度快、精度高的特点。
New supersonic and hypersonic aircrafts require aerodynamic maneuverability in the high attitude and long cruising range,which requires the aircrafts bear such configuration characteristics as large ratio of slenderness and with inlets.Newton's theory of collision methods is widely used in the calculation of aerodynamic characteristics of hypersonic blunted nose shapes,this paper extends this method to the calculation of aerodynamic characteristics of new supersonic and hypersonic aircrafts with inlets.A la...
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2008年第2期494-498,共5页
Journal of Astronautics
关键词
超/高超声速
大长细比
带进气道
气动力特性预测
Supersonic and hypersonic
Large ratio of slenderness
With inlets
Prediction of aerodynamic characteristics
