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.

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Mechanical, Aerospace and Biomedical Engineering Department,

maji@utsi.edu
Mechanical, Aerospace and Biomedical Engineering Department,

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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,

maji@utsi.edu
University of Tennessee Space Institute

, Tullahoma, TN 37388
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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

University of Tennessee Space Institute

, Tullahoma, TN 37388maji@utsi.edu

Michel Akiki

University of Tennessee Space Institute

, Tullahoma, TN 37388*J. 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

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Theory of Solid-Propellant Nonsteady Combustion