The non-reactive and reactive flows through a model scramjet were investigated using a Improved Delayed Detached Eddy Simulation(IDDES), which is one of the hybrid schemes of Reynold averaged Navier-Stokes equation and large eddy simulation, and flamelet combustion model. Geometries and boundary conditions of scramjet combustor conducted by DLR, German Aerospace Center were considered. The model scramjet combustor consists of 15 holes for hydrogen injection located on the base of a wedge shaped fuel injector providing hydrogen at sonic speed. In this paper, only one of the 15 injection holes was considered, and periodic condition is applied in the spanwise dirction. The parametric studies were conducted with a view to invesitigate better numerical configurations, for example, MUSCL or WENO as convective flux schemes and k-ω SST or IDDES as turbulence models with steady flamelet combustion model. The combination of WENO and IDDES provides best one for reacting case. NomenclatureD k = turbulent kinetic energy destruction term E = specific total energy f = mixture fraction h = specific enthalpy k = turbulent kinetic energy l = length scale M t = turbulent mach number p = static pressure P k = turbulence kinetic energy production term q j = specific heat flux t = time T = temperature u = velocity x = spatial coordinate Y = species mass concentraion δ ij = Kronecker delta μ = molecular viscosity μ t = turbulent viscosity ρ = density τ ij = viscous stress tensor ω = turbulent frequency Superscripts ‾ = time averaged quantity ~ = Favre averaged quantity 1 Graduate Research Assistant, School of Aerospace and Mechanical Engineering 2 Professor, School of Aerospace and Mechanical Engineering; hgsung@kau.kr. Associate Fellow AIAA Downloaded by UNIVERSITY OF ILLINOIS on October 1, 2015 | http://arc.aiaa.org |
A new modeling concept to predict internal flow structures in scramjet isolator has been introduced. The analytical model proposed in this study consists of mean and fluctuation parts to predict local flow properties in the isolator. The isolator model has been favorably compared with CFD results and experimental data. The CFD considered a typical hypersonic intake and isolator with constant flow channel area and took account of boundary layer effect. The model was applied to various isolator geometry with several inlet flow conditions. NomenclatureA = Area dt = time step H = height i = time index during navigation j = waypoint index M = Mach number p = static Pressure q = gas dynamic function t = time X = distance after the first induced shock wave in isolator = compression angle = Specific heat ratio cowl = cowl angle ij = viscous stress tensor = angle of shock wave, period of shock wave reflection
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