Numerical simulation of inlet and combustor regions of a real shcramjet flowfield.
Published: 2005
Language: eng
Number of pages: 63
Description: This thesis addresses the problem of designing a shock-induced combustion ramjet (shcramjet) engine. Previous studies have investigated cantilevered ramp injectors using a two oblique shock external compression inlet with a hydrogen slot injector to suppress ignition. The present study uses a cowl to generate flow-turning angles of 12&deg; and 16&deg;. The reflected shocks induce combustion after ignition delays of 10.5 cm and 4.5 cm, respectively. It was found that maximum thrust potentials for each case were 203.4 and 218.8  Ns/kg, indicating that an increase in shock strength reduces the ignition delay without contributing to any significant increase in thrust potential.The numerical simulation of the three-dimensional flowfield of a shcramjet was performed using the WARP code, in which multispecies Favre-averaged Navier-Stokes equations are closed by the k-o turbulence model and the Wilcox dilational dissipation correction. The hydrogen/air chemical reactions are modeled by Jachimowsky's 9 species, 20 reaction model.
Notes: Source: Masters Abstracts International, Volume: 44-01, page: 0422.

Thesis (M.A.Sc.)--University of Toronto, 2005.

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