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

Sung In Kim, Ibrahim Hassan

Research output: Contribution to conferencePaperpeer-review

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
Pages267-276
DOIs
Publication statusPublished - 2010
EventASME 2010 International Mechanical Engineering Congress and Exposition - Vancouver, Canada
Duration: 12 Nov 201018 Nov 2010

Conference

ConferenceASME 2010 International Mechanical Engineering Congress and Exposition
CountryCanada
CityVancouver
Period12/11/201018/11/2010

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