Numerical Study of Film Cooling Scheme on a Blunt-Nosed Body in Hypersonic Flow

Sung In Kim, Ibrahim Hassan

Research output: Contribution to journalArticlepeer-review

5 Citations (Scopus)


In hypersonic flight, 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 of gas turbine engines, 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 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
Article number044501
Number of pages7
JournalJournal of Thermal Science and Engineering Applications
Issue number4
Early online date13 Oct 2011
Publication statusPublished - 01 Dec 2011


  • film cooling
  • hypersonic flow
  • thermal protection system
  • blunt body
  • CFD

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