Wind Tunnel Investigation of the Transonic Aerodynamic Characteristics of a Full-Scale Flight Path Accelerometer (Follow-On Test).
ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AIR FORCE STATION TENN
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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.
- Test Facilities, Equipment and Methods