Test flow evaluation in shock wind tunnel and Development of heat flux sensor

2015 Fiscal Year Final Research Report

• Project/Area Number: 26820375
• Research Category: Grant-in-Aid for Young Scientists (B)
• Allocation Type: Multi-year Fund
• Research Field: Aerospace engineering
• Research Institution: Japan Aerospace EXploration Agency
• Principal Investigator: Takayanagi Hiroki 国立研究開発法人宇宙航空研究開発機構, 研究開発部門, 研究員 (70513422)
• Co-Investigator(Renkei-kenkyūsha): NOMURA Satoshi 宇宙航空研究開発機構, 航空部門・空力技術研究ユニット, 研究員 (80709361) ; FUJITA Kazuhisa 宇宙航空研究開発機構, 研究開発部門・第2研究ユニット, 主幹研究員 (90281584)
• Project Period (FY): 2014-04-01 – 2016-03-31
• Keywords: 航空宇宙流体力学

Outline of Final Research Achievements

In　order　to　evaluate　radiation　intensity　spectrum　from　shock　layer　in　shock　wind　tunnel　test　flow, radiation analysis code, SPRADIAN 2, was updated to simulate the atomic lines of metallic species.　The number density of metallic impurities are found to be more than two orders of magnitude lower than those of atomic oxygen and nitrogen. The temperature is approximately estimated at 7500K. The radiative heat flux is 22.5MW/m2 with the emissivity of unity. In addition, a heat flux sensor with coaxial thermocouple has been made and tested in hypervelocity expansion tube. Heat flux was estimated as about 5MW/m2 by temperature increase. Applied velocity region will be improved by protection against noise.

Free Research Field

航空宇宙工学