Accession Number:

ADA532847

Title:

HIFiRE Flight 2 Flowpath Design Update (PREPRINT)

Descriptive Note:

Conference paper preprint

Corporate Author:

AIR FORCE RESEARCH LAB WRIGHT-PATTERSON AFB OH PROPULSION DIRECTORATE

Report Date:

2009-12-01

Pagination or Media Count:

17.0

Abstract:

This paper describes the evolution of various aspects of the flowpath design as the payload system design has matured. Forebody design changes were required in order to reduce the overall payload system weight and to meet shroud design requirements. In response to the forebody design changes, modifications were made to the fuel injectors within the combustor as the captured air mass flow rate reduced. No additional changes were made to the isolatorcombustor relative to the baseline flowpath. Forebody design changes allowed the nozzle design to be adjusted resulting in additional payload weight and length reductions. Finally, in an attempt to mitigate any adverse effects during the boost phase of the flight trajectory, stationary covers were designed to protect the scramjet nozzle exit regions. Each of these modifications will be described in this paper along with relevant analysis results to illustrate the effects on the overall payload system. The updated instrumentation plan for the current payload system will also be described.

Subject Categories:

  • Rockets
  • Jet and Gas Turbine Engines
  • Rocket Engines
  • Rocket Propellants

Distribution Statement:

APPROVED FOR PUBLIC RELEASE