2020 年 18 巻 1 号 p. 1-7
The aerodynamic characteristics of a small-size hypersonic experimental aircraft called HIMICO are numerically simulated using CFD. A wide range of angles of attack and side-slip angles in Mach-5 flows are investigated, and the results are compared with wind-tunnel tests (WTT). Dynamic stability derivatives are also estimated using CFD. The flight trajectories are then calculated based on the aerodynamic coefficients obtained using CFD. The effects of aerodynamic damping due to the dynamic stability derivatives are large, especially on the attitude of the aircraft with an initial roll/yaw angle deviating from the nominal. Even so, the important criteria for the engine test are satisfied by both results under the assumed initial conditions. Validation of the simulation methods developed for designing hypersonic aircrafts was confirmed.
