In this work, we present two simple mean flow solutions that mimic the bulk gas motion inside a full-length, cylindrical hybrid rocket engine. Two distinct methods are used. The first is based on steady, axisymmetric, rotational, and incompressible flow conditions. It leads to an Eulerian solution that observes the normal sidewall mass injection condition while assuming a sinusoidal injection profile at the head end wall. The second approach constitutes a slight improvement over the first in its inclusion of viscous effects. At the outset, a first order viscous approximation is constructed using regular perturbations in the reciprocal of the wall injection Reynolds number. The asymptotic approximation is derived from a general similarity reduced Navier–Stokes equation for a viscous tube with regressing porous walls. It is then compared and shown to agree remarkably well with two existing solutions. The resulting formulations enable us to model the streamtubes observed in conventional hybrid engines in which the parallel motion of gaseous oxidizer is coupled with the cross-streamwise (i.e., sidewall) addition of solid fuel. Furthermore, estimates for pressure, velocity, and vorticity distributions in the simulated engine are provided in closed form. Our idealized hybrid engine is modeled as a porous circular-port chamber with head end injection. The mathematical treatment is based on a standard similarity approach that is tailored to permit sinusoidal injection at the head end.
Skip Nav Destination
e-mail: maji@utsi.edu
Article navigation
October 2010
Research Papers
Rotational and Quasiviscous Cold Flow Models for Axisymmetric Hybrid Propellant Chambers
Joseph Majdalani,
Joseph Majdalani
H. H. Arnold Chair of Excellence in Advanced Propulsion and Professor
Mechanical, Aerospace and Biomedical Engineering Department,
e-mail: maji@utsi.edu
University of Tennessee Space Institute
, Tullahoma, TN 37388
Search for other works by this author on:
Michel Akiki
Michel Akiki
Mechanical, Aerospace and Biomedical Engineering Department,
University of Tennessee Space Institute
, Tullahoma, TN 37388
Search for other works by this author on:
Joseph Majdalani
H. H. Arnold Chair of Excellence in Advanced Propulsion and Professor
Mechanical, Aerospace and Biomedical Engineering Department,
University of Tennessee Space Institute
, Tullahoma, TN 37388e-mail: maji@utsi.edu
Michel Akiki
Mechanical, Aerospace and Biomedical Engineering Department,
University of Tennessee Space Institute
, Tullahoma, TN 37388J. Fluids Eng. Oct 2010, 132(10): 101202 (7 pages)
Published Online: October 12, 2010
Article history
Received:
May 2, 2009
Revised:
August 16, 2010
Online:
October 12, 2010
Published:
October 12, 2010
Citation
Majdalani, J., and Akiki, M. (October 12, 2010). "Rotational and Quasiviscous Cold Flow Models for Axisymmetric Hybrid Propellant Chambers." ASME. J. Fluids Eng. October 2010; 132(10): 101202. https://doi.org/10.1115/1.4002397
Download citation file:
Get Email Alerts
Switching Events of Wakes Shed From Two Short Flapping Side-by-Side Cylinders
J. Fluids Eng (May 2025)
Related Articles
Investigation of Heat Transfer and Scale Effects on the Performance of a Giffard Injector-Pumped Microrocket
J. Thermal Sci. Eng. Appl (December,2011)
Thermodynamic Effect on a Cavitating Inducer in Liquid Hydrogen
J. Fluids Eng (November,2010)
Experimental Study on Temperature Change by Cavitation Accompanying Self-Pressurization of Propellant for Small Rocket Engines
J. Fluids Eng (December,2021)
Liquid Rocket Engine Feed System Dynamics by the Method of Characteristics
J. Eng. Ind (November,1968)
Related Proceedings Papers
Related Chapters
Steady-state Combustion
Theory of Solid-Propellant Nonsteady Combustion
The Influence of Liquid Rocket Engine Inducer Compliance and Mass Flow Gain Factor on Cavitation Surge Frequencies
Proceedings of the 10th International Symposium on Cavitation (CAV2018)
Back Matter
Theory of Solid-Propellant Nonsteady Combustion