Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave

Abstract An array of subsonic counter-flow jets is studied as an active thermal protection system (TPS) for wing leading edges of hypersonic vehicles. The performance is numerically estimated in the model case of a circular cylinder on the basis of the 2D compressible Navier-Stokes equations. In con...

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Bibliographic Details
Main Authors:	Taku Ohwada, Tomonori Shimada, Takuma Kato
Format:	Article
Language:	English
Published:	SpringerOpen 2019-01-01
Series:	Advances in Aerodynamics
Subjects:	Counter-flow jet Hypersonic vehicle Thermal protection system Compressible Navier-Stokes Shock capturing
Online Access:	http://link.springer.com/article/10.1186/s42774-019-0001-z

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record_format	Article
spelling	doaj-0ddf3f781c484839872ab6c803641e892020-11-25T02:37:26ZengSpringerOpenAdvances in Aerodynamics2524-69922019-01-011111310.1186/s42774-019-0001-zNumerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock waveTaku Ohwada0Tomonori Shimada1Takuma Kato2Department of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto UniversityDepartment of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto UniversityDepartment of Aeronautics and Astronautics, Graduate School of Engineering, Kyoto UniversityAbstract An array of subsonic counter-flow jets is studied as an active thermal protection system (TPS) for wing leading edges of hypersonic vehicles. The performance is numerically estimated in the model case of a circular cylinder on the basis of the 2D compressible Navier-Stokes equations. In contrast to a single subsonic jet, an array of jets is robust against variation of the angle of attack; high cooling effectiveness is confirmed up to 5° variation. The coolant gas (air) discharged from channels embedded in the cylinder covers over a wide range of the front surface of the cylinder. The feasibility of the active TPS is also discussed.http://link.springer.com/article/10.1186/s42774-019-0001-zCounter-flow jetHypersonic vehicleThermal protection systemCompressible Navier-StokesShock capturing
collection	DOAJ
language	English
format	Article
sources	DOAJ
author	Taku Ohwada Tomonori Shimada Takuma Kato
spellingShingle	Taku Ohwada Tomonori Shimada Takuma Kato Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave Advances in Aerodynamics Counter-flow jet Hypersonic vehicle Thermal protection system Compressible Navier-Stokes Shock capturing
author_facet	Taku Ohwada Tomonori Shimada Takuma Kato
author_sort	Taku Ohwada
title	Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave
title_short	Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave
title_full	Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave
title_fullStr	Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave
title_full_unstemmed	Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave
title_sort	numerical investigation of an active tps for a wing leading edge exposed to high temperature air behind a strong bow shock wave
publisher	SpringerOpen
series	Advances in Aerodynamics
issn	2524-6992
publishDate	2019-01-01
description	Abstract An array of subsonic counter-flow jets is studied as an active thermal protection system (TPS) for wing leading edges of hypersonic vehicles. The performance is numerically estimated in the model case of a circular cylinder on the basis of the 2D compressible Navier-Stokes equations. In contrast to a single subsonic jet, an array of jets is robust against variation of the angle of attack; high cooling effectiveness is confirmed up to 5° variation. The coolant gas (air) discharged from channels embedded in the cylinder covers over a wide range of the front surface of the cylinder. The feasibility of the active TPS is also discussed.
topic	Counter-flow jet Hypersonic vehicle Thermal protection system Compressible Navier-Stokes Shock capturing
url	http://link.springer.com/article/10.1186/s42774-019-0001-z
work_keys_str_mv	AT takuohwada numericalinvestigationofanactivetpsforawingleadingedgeexposedtohightemperatureairbehindastrongbowshockwave AT tomonorishimada numericalinvestigationofanactivetpsforawingleadingedgeexposedtohightemperatureairbehindastrongbowshockwave AT takumakato numericalinvestigationofanactivetpsforawingleadingedgeexposedtohightemperatureairbehindastrongbowshockwave
_version_	1724795651461480448

Numerical investigation of an active TPS for a wing leading edge exposed to high temperature air behind a strong bow shock wave

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