摘要
一种计算方法可用于确定带进气道的翼身组合体纵向亚声速气动特性。计算中,忽略了粘性影响,采用线化小扰动假设,根据基本解迭加的方法,求出了带进气道的翼身组合体的表面压力分布、法向力和俯仰力矩系数并给出了算例。算例结果表明:在上述假设下,进气速度比对于全弹压力分布有影响,主要是在进气道附近,进气速度比对全弹法向力和俯仰力矩的影响较小,在初步设计时可以忽略。
The Computation method of the subsonic longitudinalaerodynamic character for wing-body combination with inlet ispresented.It is assumed that the viscous effects can be neglected.Under the assumption of linearized small perturbation potential flow,the basic solution superposition is used to determinate the surfacepressure distribution,the normal force and pitching moment coefficients.The computing example is presented.The results obtained show thatunder the above assumption the inlet velocity ratio effects the surfacepressure distribution,especially at the region near the inlet,but itseffect on normal force and pitching moment can be neglected in preli-minary design.
关键词
气动计算
翼身组合体
进气道
aerodynamic computation
wing-body combination
inlet
pressure distribution
aerodynamic coefficient
linearized potential flow
