15 - Guest lectures
MACH 5 WIND TUNNEL TEST OF HIGH-MACH INTEGRATED CONTROL EXPERIMENT AIRCRAFT (HIMICO)
H. Taguchi, Tokio University of Science, Japan; T. Sato¹, C. Fujio¹, M. Tsue², T. Tsuchiya², S. Nakaya², K. Takizawa², A. Matsuo, Keio University, Japan; T. Hirotani³, H. Takahashi³, M. Hongoh³, A. Tezuka¹; ¹Waseda University, Japan ;²University of Tokyo, Japan ;³JAXA, Japan
MACH 5 WIND TUNNEL TEST OF HIGH-MACH INTEGRATED Mach 5 wind tunnel tests were conducted on the hypersonic integrated control experimental aircraft (HIMICO). Aerodynamic performance of the aircraft was obtained by hypersonic wind tunnel experiments and CFD analyses. Structural feasibility in a high-temperature flight environment was confirmed by fluid-structure coupling simulation and structural analyses. The control law of hypersonic air intake was confirmed by hypersonic wind tunnel test. The control law of hydrogen ram combustor was confirmed by direct connect combustion experiments. The aerodynamic force measurements and flow field measurements for propulsion wind tunnel tests with Mach 5 flight simulating condition were conducted with an airframe / propulsion integrated model.