2023 Volume 1 Article ID: 60
A small-scale supersonic flight experiment vehicle (OHWASHI) is being developed at Muroran Institute of Technology as a flying testbed for verification of innovative technologies for high-speed atmospheric flights which are essential to nextgeneration aerospace transportation systems. Dynamic derivatives due to angular rates of attitude motion are essential for the analysis of the six-degree-of-freedom flight path and the design of autonomous guidance and control systems for the experiment vehicle. They have been evaluated by subsonic wind-tunnel tests and CFD analysis. In this study, mechanism of dynamic derivatives due to roll and yaw rates is investigated by comparing smoke-wire visualization and CFD analysis. As a result, followings are confirmed: For 𝐶lr in the shorter-nose configuration, i.e. Nose-A, the lateral difference in the vortex flow on the main wing generates a rolling moment in the direction opposite to the yaw motion. For Cnr in the Nose-A configuration, the vertical tail has a narrower streamline spacing on its left side, which will degrade the yaw damping. In the longer-nose configuration, i.e. Nose-C, the streamline spacing is narrower on the right side of the vertical tail, which would cause yaw damping enhancement. For 𝐶lp, roll damping is considered to take place due to pressure difference between the right and left main wings.
