Wind Tunnel Investigation of the Transonic Aerodynamic Characteristics of a Full-Scale Flight Path Accelerometer (Follow-On Test)

摘要

A wind tunnel investigation was conducted on a full-scale flight path accelerometer (FPA), to eliminate shock interaction effects between the angle-of-attack and sideslip vanes and to determine angle-of-attack and angle-of-sideslip vane position errors. The shock interference effects were controlled by increasing the axial separation distance between the angle-of-attack and sideslip vanes.