Measurement of flowfield in a simulated solid-propellant ducted rocket combustor using laser Doppler velocimetry

Conference · Sat Dec 31 23:00:00 EST 1988

OSTI ID:5572848

Hsieh, W H; Yang, V; Chuang, C L; Yang, A S; Cherng, D L

A two-component LDV system was used to obtain detailed flow velocity and turbulence measurements in order to study the flow characteristics in a simulated solid-propellant ducted rocket combustor. The vortical structures near the dome region, the size of the recirculation zone, and the location of the reattachment point are all shown to be strongly affected by the jet momentum of both ram air and fuel streams. It is found that the turbulence intensity is anisotropic throughout the front portion of the simulated conbustor, and that the measured Reynolds stress conmponent distribution is well correlated with the local mean velocity vector distribution. 25 refs.

• OSTI ID: 5572848
• Report Number(s): AIAA-Paper--89-2789; CONF-8907118--
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
420200* -- Engineering-- Facilities
Equipment
& Techniques
COMBUSTION CHAMBERS
COMBUSTORS
ENGINES
FLUID FLOW
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MEASURING INSTRUMENTS
PROPELLANTS
RAMJET ENGINES
ROCKET ENGINES
TURBULENT FLOW
VELOCIMETERS
VELOCITY