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

Sung In Kim, Ibrahim Hassan

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

2 Citations (Scopus)

Abstract

In hypersonic flights, the prediction of aerodynamic heating and the construction of a proper thermal protection system (TPS) are significantly important. In this study, the method of a film cooling technique, which is already the state of the art in cooling gas turbine engine, is proposed for a fully reusable and active TPS. Effectiveness of the film cooling scheme to reduce convective heating rates for a blunt nosed spacecraft flying at Mach number 6.56 and 40 degree angle of attack is investigated numerically. The inflow boundary conditions used the standard values at an altitude of 30 km. 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 each other. 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
Title of host publicationASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010
Pages267-276
Number of pages10
Volume7
EditionPARTS A AND B
DOIs
Publication statusPublished - 2010
Externally publishedYes
EventASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010 - Vancouver, BC, Canada
Duration: 12 Nov 201018 Nov 2010

Other

OtherASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010
CountryCanada
CityVancouver, BC
Period12/11/1018/11/10

Fingerprint

Hypersonic flow
Cooling
Aerodynamic heating
Hypersonic aerodynamics
Angle of attack
Blow molding
Heating rate
Mach number
Gas turbines
Spacecraft
Turbines
Boundary conditions

ASJC Scopus subject areas

  • Mechanical Engineering

Cite this

Kim, S. I., & Hassan, I. (2010). Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow. In ASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010 (PARTS A AND B ed., Vol. 7, pp. 267-276) https://doi.org/10.1115/IMECE2010-40496

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

ASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010. Vol. 7 PARTS A AND B. ed. 2010. p. 267-276.

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

Kim, SI & Hassan, I 2010, Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow. in ASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010. PARTS A AND B edn, vol. 7, pp. 267-276, ASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010, Vancouver, BC, Canada, 12/11/10. https://doi.org/10.1115/IMECE2010-40496
Kim SI, Hassan I. Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow. In ASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010. PARTS A AND B ed. Vol. 7. 2010. p. 267-276 https://doi.org/10.1115/IMECE2010-40496
Kim, Sung In ; Hassan, Ibrahim. / Numerical study of film cooling scheme on a blunt-nosed body in hypersonic flow. ASME 2010 International Mechanical Engineering Congress and Exposition, IMECE 2010. Vol. 7 PARTS A AND B. ed. 2010. pp. 267-276
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