Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow

Sung In Kim, Ibrahim Hassan

Research output: Contribution to journalArticle

5 Citations (Scopus)

Abstract

In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are sig-nificantly important. In this study, the method of a film cooling tech-nique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effective-ness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.

Original languageEnglish
Pages (from-to)1-7
Number of pages7
JournalJournal of Thermal Science and Engineering Applications
Volume3
Issue number4
DOIs
Publication statusPublished - 1 Jan 2011

Fingerprint

blunt bodies
film cooling
hypersonic flow
Hypersonic flow
Cooling
thermal protection
hypersonic flight
aerodynamic heating
gas turbine engines
cooling
angle of attack
blowing
Aerodynamic heating
Mach number
spacecraft
slabs
Hypersonic aerodynamics
Angle of attack
Blow molding
flight

ASJC Scopus subject areas

  • Materials Science(all)
  • Condensed Matter Physics
  • Engineering(all)
  • Fluid Flow and Transfer Processes

Cite this

Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow. / Kim, Sung In; Hassan, Ibrahim.

In: Journal of Thermal Science and Engineering Applications, Vol. 3, No. 4, 01.01.2011, p. 1-7.

Research output: Contribution to journalArticle

@article{c7f66e126afe402c9170705726bc6cf9,
title = "Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow",
abstract = "In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are sig-nificantly important. In this study, the method of a film cooling tech-nique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effective-ness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.",
author = "Kim, {Sung In} and Ibrahim Hassan",
year = "2011",
month = "1",
day = "1",
doi = "10.1115/1.4005052",
language = "English",
volume = "3",
pages = "1--7",
journal = "Journal of Thermal Science and Engineering Applications",
issn = "1948-5085",
publisher = "American Society of Mechanical Engineers(ASME)",
number = "4",

}

TY - JOUR

T1 - Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow

AU - Kim, Sung In

AU - Hassan, Ibrahim

PY - 2011/1/1

Y1 - 2011/1/1

N2 - In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are sig-nificantly important. In this study, the method of a film cooling tech-nique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effective-ness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.

AB - In hypersonic flight, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are sig-nificantly important. In this study, the method of a film cooling tech-nique, which is already the state of the art in cooling of gas turbine engines, is proposed for a fully reusable and active TPS. Effective-ness of the film cooling scheme to reduce convective heating rates for a blunt-nosed spacecraft flying at Mach number 6.56 and 40 deg angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. The computational domain consists of infinite rows of film cooling holes on the bottom of a blunt-nosed slab. Laminar and several turbulent calculations have been performed and compared. The influence of blowing ratios on the film cooling effectiveness is investigated. The results exhibit that the film cooling technique could be an effective method for an active cooling of blunt-nosed bodies in hypersonic flows.

UR - http://www.scopus.com/inward/record.url?scp=84971270550&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84971270550&partnerID=8YFLogxK

U2 - 10.1115/1.4005052

DO - 10.1115/1.4005052

M3 - Article

VL - 3

SP - 1

EP - 7

JO - Journal of Thermal Science and Engineering Applications

JF - Journal of Thermal Science and Engineering Applications

SN - 1948-5085

IS - 4

ER -