Conceptual Study on hypersonic airplanes using pre-cooled turbojet

Hideyuki Taguchi, Akira Murakami, Tetsuya Sato, Takeshi Tsuchiya

Research output: Chapter in Book/Report/Conference proceedingConference contribution

8 Citations (Scopus)

Abstract

Conceptual Study on hypersonic airplanes with Mach 5 cruising capability is performed in order to improve the speed of intercontinental air transportations. Requirements for engine performance, thrust to mass ratio and heat resistant structure are discussed. As a result, reference concept of a hypersonic airplane with pre-cooled turbojet engine with liquid hydrogen fuel is shown. Then, a small hypersonic flight experiment is planned for demonstration of Mach 5 cruising technologies. Aerodynamic shape of the experimental vehicle is examined by CFD and wind tunnel tests.

Original languageEnglish
Title of host publication15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Publication statusPublished - 2008 Dec 1
Event15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference - Dayton, OH, United States
Duration: 2008 Apr 282008 May 1

Publication series

Name15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

Conference

Conference15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
CountryUnited States
CityDayton, OH
Period08/4/2808/5/1

ASJC Scopus subject areas

  • Engineering(all)

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  • Cite this

    Taguchi, H., Murakami, A., Sato, T., & Tsuchiya, T. (2008). Conceptual Study on hypersonic airplanes using pre-cooled turbojet. In 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference [2008-2503] (15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference).