民用飞机总压探头布局位置气动分析方法

民用飞机通过机载大气数据传感器测量飞机所处环境下的大气总压与静压，并计算空速。为研究民用飞机总压传感器布局位置的气动特性，采用CFD数值计算手段得到不同迎角和侧滑角工况下机头附近的流场，通过候选总压探头布局位置的局部气流角度和探头总压损失曲线获得不同工况下的总压损失和空速误差。当局部角度曲线斜率低且各曲线聚集时，是总压探头的理想最优布局位置，探头局部气流角对迎角和侧滑角均不敏感，能同时保证横向和纵向气动特性最优；通过探头位置的局部气流角度并结合风洞试验获得的总压损失系数分布曲线进行总压损失预估，该方法对总压损失的预测准确有效,预测精度满足要求，可用来进行空速误差估算；总压探头布局位置的选取需结合民用飞机实际运行的侧滑角/迎角包线综合判断。

Aerodynamic analysis method of total pressure probe layout of civil aircraft

The total atmospheric pressure and static pressure in the environment of civil aircraft are measured by airborne air data sensors, and the airspeed can be calculated. In order to investigate aerodynamic characteristics of the total pressure probe layout location of civil aircraft, the flow field near the nose under different angles of attack and sideslip angles was obtained by CFD numerical calculation. Total pressure loss and airspeed error under different working conditions can be derived from local flow direction located on total-pressure probe and total pressure coefficient distribution. Results show that the layout position at which the local flow angle distribution curves are flat and compact is optimal for total pressure probe, and the local flow angle is insensitive to the angles of attack and sideslip. The yaw and pitch characteristics of the aircraft comes to an optimal solution. The prediction method in this paper works well in terms of effectiveness and accuracy, and the prediction accuracy agrees well with the total pressure probe measurement requirement. The airspeed error can be calculated correctly. Angle envelope of sideslip and attack should be considered when analyzing aerodynamic layout position of total pressure probe.