A Method for Measuring Damping-in-Pitch of Models in Supersonic Flow.

摘要

A technique has been developed to measure the damping-in-pitch of bodies of revolution in the Supersonic Wind Tunnel over a Mach number range of 1.75 to 4.5. The angular position of the model at any time is recorded with an oscillograph. The aerodynamic damping moments are computed from measurements of the rate of subsidence of the angle of attack. (Author)