机头波纹度对全静压探头测孔压强的影响

准确掌握飞机机头波纹度对全静压探头周围绕流及测孔压强的影响规律，对于提高飞机高度测量系统自身精度及其误差分析具有重要意义。论文采用计算流体力学方法，开展了机头波纹度对全静压探头测孔压强的影响规律研究。针对单独探头构型，进行了数值模拟方法的验证。针对单独机头构型，研究了波纹度对探头预安装位置附近的空间区域压强的影响规律。针对探头与理论机头和波纹度机头的组合构型，研究了波纹度对全静压探头绕流及测孔处压强的影响规律。结果表明：文中数值模拟方法能够满足机头全静压探头流场的数值模拟要求；波纹度对探头测孔处压强系数的影响变化量随着马赫数增加而增加；当马赫数固定时，波纹度的影响在第一组测压孔处随迎角增大而减弱，而在第二组测压孔处随迎角增大先增加再减弱。

Study on the influence of nose skin waviness on the hole pressure of the total static pressure probe

It is of great significance for improving the precision and error analysis of the aircraft altitude measurement system to accurately understand the influence of aircraft nose skin waviness on the flow around the total static pressure probe and the pressure of the measuring hole. In this paper, the effect of the nose skin waviness on the hole pressure of the full static pressure probe is studied by using computational fluid dynamics method. The numerical simulation method is verified based on the single probe configuration. For a single aircraft nose configuration, the influence of skin waviness on the pressure in the spatial area near the pre-installation position of the probe is studied. For the combination configuration of the probe and aircraft noses, including the theoretical aircraft nose and the waviness nose, the influence of the skin waviness on the flow around the total static pressure probe and the pressure at the measuring hole is studied. The results show that the numerical simulation method can meet the requirements of the numerical simulation of the flow field around the total static pressure probe on the nose surface. The influence of the waviness on the pressure coefficient at the measuring hole of the probe increases with the increase of Mach number. For a fixed Mach number, the influence of waviness decreases with the increase of the angle of attack at the first group of pressure measuring holes, and increases first and then decreases with the increase of the angle of attack at the second group of pressure measuring holes.