NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Vortex shedding from solid rocket propellant inhibitorsVortex shedding frequency caused by the protrusion of inhibitors into the flow field of a solid rocket motor is investigated by experimental and mathematical models. The time dependent Navier-Stokes equations are solved using a finite difference technique assuming incompressible, two-dimensional flow under both laminar and turbulent flow conditions. For laminar flow, explicit solutions are obtained using a vorticity-transport equation in place of the Navier-Stokes equations. For turbulent flow, a two-equation (k-epsilon) model is used for turbulent modeling and the SIMPLE algorithm is employed as the computational scheme. Cold flow tests were conducted to confirm the basic flow structure and to determine the vortex shedding frequency under both laminar and turbulent flow conditions. The vortex shedding frequencies were determined using a stroboscope to measure the oscillating frequency of yarn tufts which were fastened to one inhibitor in the models. A hot-film anemometer established the velocity history behind the inhibitor. Good agreement between the theoretical results and measurements of the vortex shedding frequencies is demonstrated.
Document ID
19860057890
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Shu, P. H.
(Auburn Univ. AL, United States)
Sforzini, R. H.
(Auburn Univ. AL, United States)
Foster, W. A., Jr.
(Auburn University AL, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1986
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 86-1418
Accession Number
86A42628
Funding Number(s)
CONTRACT_GRANT: NAS8-36147
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available