TY - GEN
T1 - Mach 4 propulsion wind tunnel test of high-mach integrated control experimental aircraft (Himico)
AU - Taguchi, Hideyuki
AU - Hirotani, Tomonari
AU - Takahashi, Hidemi
AU - Oki, Junichi
AU - Sato, Tetsuya
AU - Tezuka, Asei
AU - Tsue, Mitsuhiro
AU - Tsuchiya, Takeshi
AU - Nakaya, Shinji
AU - Matsuo, Akiko
N1 - Funding Information:
This research was conducted using the experimental aircraft model produced by a scientific research grant (representative: Professor Sato of Waseda University) . The wind tunnel experiment was conducted collaborating with PD Aerospace under the Space Innovation Partnership (J-SPARC) of the JAXA New Business Promotion Department. The authors acknowledge the contribution of the following researchers: Dr. Tomioka, Dr. Ueda, Dr. Tani, Mr. Kato, and others at JAXA Kakuda Space Center, Dr. Ishii, Dr. Kojima, Mr. Hongoh and others at JAXA Chofu Aerospace Center. Dr. Hiruma, Dr. Morita, Mr. Kayama, Mr. Tanaka, Mr. Fukazawa, Mr. Iba, Mr. Arai, Mr. Ikeda, Mr. Omi, Mr. Chiga, Mr. Ogura, Mr. Fujii, Ms. Fujii, Mr. Yoshihara as JAXA technical trainees. Professors and students at HIMICO Study Group.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - Mach 4 propulsion wind tunnel experiment of High Mach Integrated Control Experimental Aircraft (HIMICO) has been conducted in order to evaluate the installed performance of hypersonic engine, which is operated by hydrogen fuel. Surface temperature of the airframe, total pressure recovery of hypersonic air intake, temperature field around the exhaust nozzle, and longitudinal aerodynamic forces are measured in the experiment. The effect of the flow field around the airframe to the hypersonic engine performance and the effect of the engine exhaust to the aerodynamic forces are discussed based on the experimental results.
AB - Mach 4 propulsion wind tunnel experiment of High Mach Integrated Control Experimental Aircraft (HIMICO) has been conducted in order to evaluate the installed performance of hypersonic engine, which is operated by hydrogen fuel. Surface temperature of the airframe, total pressure recovery of hypersonic air intake, temperature field around the exhaust nozzle, and longitudinal aerodynamic forces are measured in the experiment. The effect of the flow field around the airframe to the hypersonic engine performance and the effect of the engine exhaust to the aerodynamic forces are discussed based on the experimental results.
UR - http://www.scopus.com/inward/record.url?scp=85121268187&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=85121268187&partnerID=8YFLogxK
U2 - 10.2514/6.2021-4196
DO - 10.2514/6.2021-4196
M3 - Conference contribution
AN - SCOPUS:85121268187
SN - 9781624106125
T3 - Accelerating Space Commerce, Exploration, and New Discovery conference, ASCEND 2021
BT - Accelerating Space Commerce, Exploration, and New Discovery conference, ASCEND 2021
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - Accelerating Space Commerce, Exploration, and New Discovery conference, ASCEND 2021
Y2 - 15 November 2021 through 17 November 2021
ER -