摘要
提出了基准流场与唇口平面形状分步优化的高超声速内收缩进气道设计方法。基准流场以反射激波不均匀性最小和总压恢复最大进行多目标优化设计,使用结合Tayler-Maccoll方程的有旋特征线方法(MOC)进行流场计算,获得双拐点母线内收缩锥基准流场。进气道唇口形状以沿流线积分(Streamline Integral Method,SIM)获得的进气道无黏阻力最小为目标进行优化设计,获得类椭圆形唇口平面形状。针对优化设计结果进行数值模拟,与传统直母线基准流场相比,双拐点母线基准流场反射激波后流动不均匀性下降40%左右,总压损失减少35%左右,总体性能提升明显。类椭圆唇口进气道在设计点的单位质量流量无黏阻力相较于圆形唇口降低6%,具有良好的压缩特性和气动效率,能够减弱进气系统对飞行器气动性能的不利影响。研究结果表明该方法是一种高效且实用的高超声速内收缩进气道设计方法。
Hypersonic inward turning inlet is optimized by a multistage method of separating the base flow and lip shape.Multi-objective optimization is imposed on the base flow with the target of minimizing the flow non-uniformity after the reflected shock and maximizing the total pressure recovery.The flow field has been solved by the method of characteristic(MOC)integrated with the Tayler-Maccoll equations.Base flow optimization obtains a dual-infection point internal cone's element.Inlet lip shape is optimized by the target of minimizing the inviscid drag obtained by streamline integral method(SIM)and a semi-oval two-dimensional lip shape is obtained.Compared with the traditional straight element base flow,dual-infection point internal cone flow's non-uniformity is decreased by about 40% and the total pressure loss is decreased by 35%,and thus the overall performance is enhanced significantly.Semi-oval inlet's inviscid drag per unit mass flow is decreased by 6%compared with the circle lip shape inlet at the design point,and its good compress characteristics and aerodynamic efficiency can partially get over the inlet system's adverse influence on the aerodynamic performance of vehicle.Research proves the design method of hypersonic inward turning inlet proposed in this paper is efficient and functional.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2015年第12期3759-3773,共15页
Acta Aeronautica et Astronautica Sinica
基金
省部级项目~~