滑流区中三角翼大攻角气动力特性的实验研究  

Experiment on Aerodynamic Characteristics of a Thin Delta Winged Body in Hypersonic Rarefied Flow

作　　者：陈素贞[1] 马家驩[1] 潘文欣[1] 

机构地区：[1]中国科学院力学研究所,北京100080

出　　处：《空气动力学学报》1993年第1期42-48,共7页Acta Aerodynamica Sinica

基　　金：国家自然科学基金

摘　　要：一种以后掠75.7°薄三角翼为主要特征的典型航空航天飞行器模型,在激波管风洞马赫数为11.9和15.4两种条件下,攻角范围20°～50°,用模型自由飞方法测量了它们的轴向力系数、法向力系数和俯仰力矩特性。相应的实验雷诺数分别为3.19×10~4和1.64×10~4,这两种流动条件均属于稀薄气流的滑流区。 实验结果表明在M_∞=11.9和15.4两种条件下,两种剖面外形模型的升力系数和阻力系数均随攻角加大而递增,其变化规律有很好的一致性,且对马赫数并不敏感;但从体轴系来看,不仅两种模型的轴向力系数不同,而且因粘性干扰的缘故,同一模型A在M_∞=15.4时比M_∞=11.9时有相对较大的轴向力系数,但两者随攻角变化的规律一致,且当α>45°时接近牛顿值。此外,实验表明两种模型的压心系数随攻角均没有明显变化。The aerodynamic coefficients of a thin Delta winged body were measured by free-flight method in JF-8 shock tunnel at Mach number 11.9 and 15.4, The aero-space plane like model with swept angle of 75.7° consists of two cut cones with different profile, one circle and one elliptic. The experimental condition is laid on rarefied flow with Reynolds number of 1.64~3.19×104, near to and in the slip flow regime.The experimental results show that the normal force coefficients of model A and B in two flow conditions are not sensitive to the Mach number and well agreed with the corrected Newtonian's predictions, however the axial force coefficients are different not only for two models, but also for same model at different flow conditions,the lower the Reynolds number of flow condition, the higher the axial force coefficient for the viscosity effects. The results also show that the axial force coefficients are higher than the predictions by Newtonian's theory and getting closer to the values when the angle of attack is higher than 45 degrees.

关 键 词：气动力 测量 三角翼 滑流区 飞机 

分 类 号：V212.11[航空宇航科学与技术—航空宇航推进理论与工程]