Accession Number:

ADA162111

Title:

Combustor/Inlet Interactions and Modeling of Hypersonic Dual Combustor Ramjet Engines.

Descriptive Note:

Final rept. Oct 83-Sep 84,

Corporate Author:

JOHNS HOPKINS UNIV LAUREL MD APPLIED PHYSICS LAB

Report Date:

1984-11-19

Pagination or Media Count:

57.0

Abstract:

The purpose of this research has been to experimentally and analytically describe the inletcombustorexit nozzle flowfields in hypersonic DCR Dual combustion Ramjet engines. The experimental effort to date describes, in part, the flow characteristics in the isolator duct that conducts air supersonically from the external flowfield of the hypersonic air inlet to the supersonic combustor. This description includes the mean flow properties, the turbulent fluctuation flow properties, the boundary layer growth and the simulated precombustion compression field for an initial Mach 2.4 flow in a 20-in. long annular duct with inner and outer radii of 3.125 and 4.2 in., respectively. The analytical effort includes models that describe 1 the recirculation region at the DCR gas generator base created by a surrounding supersonic jet 2 the mixing and burning processes in the DCR supersonic combustor 3 the supersonic combustor boundary layer and 4 the nozzle flow. The models include such enhancements as finite rate, multiple species chemistry, the solution of the full Navier-Stokes equations for axisymmetric flow and energy transfer due to mass diffusion. Keywords Combustorinlet interactions Shock boundary layer interactions Skin friction and heat transfer Mixing and combustion Supersonic combustion.

Subject Categories:

  • Fluid Mechanics
  • Combustion and Ignition
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE