【摘要】 基于ANSYS软件，以某高超声速飞行器钝头锥为研究对象，运用计算流体动力学（Computational Fluid Dynamics,CFD）数值模拟技术对头锥外流场气动热进行计算，分析了在高超声速来流下头锥壁面流场区空气温度、压强、速度和密度的分布规律，并运用单向流-热-固耦合对头锥进行热力耦合计算，得到头锥温度场、应力场和变形量，从而对该类型头锥防热措施提供合理的建议。更多还原

【Abstract】 Based on the ANSYS software, this paper takes a blunt nose cone of a hypersonic aircraft as the research object,uses Computational Fluid Dynamics(CFD) numerical simulation technology to calculate the aerodynamic heat of the outer flow field of the nose cone, analyzes the distribution laws of air temperature, pressure, velocity, and density in the flow field area of the nose cone wall under hypersonic inflow, and uses one-way flow thermal-solid coupling to calculate the thermal coupling of the nose cone, obtaining the temperature field, stress field, and deformation field of the nose cone, reasonable suggestions on heat prevention measures for this type of head cone are given.更多还原