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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.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° and 16°. 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.
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Subjects
Airplanes, Scramjet enginesShowing 2 featured editions. View all 2 editions?
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1
Numerical simulation of inlet and combustor regions of a real shcramjet flowfield.
2005
in English
0494024445 9780494024447
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2
Numerical simulation of inlet and combustor regions of a real shcramjet flowfield.
2005
in English
0494024445 9780494024447
|
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Libraries near you:
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Book Details
Edition Notes
Thesis (M.A.Sc.)--University of Toronto, 2005.
Electronic version licensed for access by U. of T. users.
Source: Masters Abstracts International, Volume: 44-01, page: 0422.
GERSTEIN MICROTEXT copy on microfiche (1 microfiche).
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- Created October 26, 2008
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