Accession Number:

ADA568558

Title:

Dynamics of Supercritical Flows

Descriptive Note:

Final rept. 27 Sep 2004-28 May 2012

Corporate Author:

AIR FORCE RESEARCH LAB EDWARDS AFB CA PROPULSION DIR

Report Date:

2012-08-26

Pagination or Media Count:

1211.0

Abstract:

This research has concentrated on the characterization of mixing for typical liquid rocket injectors. The conditions of interest have encompassed subcritical to supercritical pressures with temperatures below and above the critical temperature, with and without an acoustic field. The project has been largely experimental in-house. A single shear coaxial injector element has been thoroughly studied. This type of injector element is commonly used in many rocket engines e.g., Space Shuttle Main Engine SSME, Vulcain, RS-68, etc. It was found that the mixing in these injectors is governed primarily by the presence or absence of an acoustic field, the outer to inner jet area ratio and the inner jet lip thickness to inner jet diameter, the outer to inner momentum flux ratio, the reduced density of the inner jet, and on whether the pressure is subcritical and supercritical.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE