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.
|Number of pages||7|
|Journal||Journal of Thermal Science and Engineering Applications|
|Publication status||Published - 1 Jan 2011|
ASJC Scopus subject areas
- Materials Science(all)
- Condensed Matter Physics
- Fluid Flow and Transfer Processes