Accession Number:

ADA229670

Title:

Flow Establishment in a Generic Scramjet Combustor

Descriptive Note:

Contractor rept.

Corporate Author:

INSTITUTE FOR COMPUTER APPLICATIONS IN SCIENCE AND ENGINEERING HAMPTON VA

Report Date:

1990-10-01

Pagination or Media Count:

40.0

Abstract:

The establishment of a quasi-steady flow in a generic scramjet combustor is studied for the case of a time varying inflow to the combustor. Such transient flow is characteristic of the reflected-shock tunnel and expansion-tube test facilities. Several numerical simulations of hypervelocity flow through a straight-duct combustor with either a side-wall-step fuel injector or a centrally-located strut injector are presented. Comparisons are made between impulsively started but otherwise constant flow conditions typical of the expansion tube or tailored operation of the reflected-shock tunnel and the relaxing flow produced by the undertailored operation of the reflected- shock-tunnel. Generally the inviscid flow features, such as the shock pattern and pressure distribution, were unaffected by the time varying inlet conditions and approached steady state in approximately the times indicated by experimental correlations. However, viscous features, such as heat transfer and skin friction, were altered by the relaxing inlet flow conditions. Keywords Supersonic combustion ramjet engines Shock tunnels Mathematical models Air flow Jet engine inlets Heat transfer Fluid mechanics Test evaluation Supersonic flow Supersonic inlets Steady flow Unsteady flow Hypersonic velocityaerodynamics, Skin friction.

Subject Categories:

  • Test Facilities, Equipment and Methods
  • Fluid Mechanics
  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE