NASA Technical Reports Server (NTRS) : Flow pdf

NASA Technical Reports Server (NTRS) : Flow

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The establishment of a quasi-steady flow in a generic scramjet combustor was 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 were made between impulsively started but otherwise constant flow conditions (typical of the expansion tube or tailored operations of the reflected shock tunnel) and the relaxing flow produced by the ‘undertailored’ operations 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 approx. the times indicated by experimental correlations. However, viscous features, such as heat transfer and skin friction, were altered by the relaxing inlet flow conditions

• Creator/s: NASA Technical Reports Server (NTRS
• Date: 10/1/1990
• Year: 1990
• Book Topics/Themes: NASA Technical Reports Server (NTRS), FLOW DISTRIBUTION, INLET FLOW, INVISCID FLOW, SHOCK TUNNELS, SUPERSONIC COMBUSTION RAMJET ENGINES, UNSTEADY FLOW, COMBUSTION CHAMBERS, COMPUTERIZED SIMULATION, DUCTED FLOW, FUEL INJECTION, HEAT TRANSFER, HYPERVELOCITY FLOW, PRESSURE DISTRIBUTION, SKIN FRICTION, STEADY STATE, Jacobs, P. A., Rogers, R. C., Weidner, E. H., Bittner, R. D

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