Computation of turbulent reacting flow in a solid-propellant ducted rocket
Abstract
A mathematical model for computation of turbulent reacting flows is developed under general curvilinear coordinate systems. An adaptive, streamline grid system is generated to deal with the complex flow structures in a multiple-inlet solid-propellant ducted rocket (SDR) combustor. General tensor representations of the k-epsilon and algebraic stress (ASM) turbulence models are derived in terms of contravariant velocity components, and modification caused by the effects of compressible turbulence is also included in the modeling. The clipped Gaussian probability density function is incorporated in the combustion model to account for fluctuations of properties. Validation of the above modeling is first examined by studying mixing and reacting characteristics in a confined coaxial-jet problem. This is followed by study of nonreacting and reacting SDR combustor flows. The results show that Gibson and Launder`s ASM incorporated with Sarkar`s modification for compressible turbulence effects based on the general curvilinear coordinate systems yields the most satisfactory prediction for this complicated SDR flowfield. 36 refs.
- Authors:
-
- Natl Cheng Kung Univ, Tainan, Taiwan (China)
- Publication Date:
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 117649
- Resource Type:
- Journal Article
- Journal Name:
- Journal of Propulsion and Power
- Additional Journal Information:
- Journal Volume: 11; Journal Issue: 3; Other Information: PBD: May 1995
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING NOT INCLUDED IN OTHER CATEGORIES; 40 CHEMISTRY; COMPRESSIBLE FLOW; COMPUTERIZED SIMULATION; TURBULENT FLOW; FUELS; COMBUSTION; NAVIER-STOKES EQUATIONS; NUMERICAL SOLUTION
Citation Formats
Chao, Y, Chou, W, and Liu, S. Computation of turbulent reacting flow in a solid-propellant ducted rocket. United States: N. p., 1995.
Web. doi:10.2514/3.23867.
Chao, Y, Chou, W, & Liu, S. Computation of turbulent reacting flow in a solid-propellant ducted rocket. United States. https://doi.org/10.2514/3.23867
Chao, Y, Chou, W, and Liu, S. 1995.
"Computation of turbulent reacting flow in a solid-propellant ducted rocket". United States. https://doi.org/10.2514/3.23867.
@article{osti_117649,
title = {Computation of turbulent reacting flow in a solid-propellant ducted rocket},
author = {Chao, Y and Chou, W and Liu, S},
abstractNote = {A mathematical model for computation of turbulent reacting flows is developed under general curvilinear coordinate systems. An adaptive, streamline grid system is generated to deal with the complex flow structures in a multiple-inlet solid-propellant ducted rocket (SDR) combustor. General tensor representations of the k-epsilon and algebraic stress (ASM) turbulence models are derived in terms of contravariant velocity components, and modification caused by the effects of compressible turbulence is also included in the modeling. The clipped Gaussian probability density function is incorporated in the combustion model to account for fluctuations of properties. Validation of the above modeling is first examined by studying mixing and reacting characteristics in a confined coaxial-jet problem. This is followed by study of nonreacting and reacting SDR combustor flows. The results show that Gibson and Launder`s ASM incorporated with Sarkar`s modification for compressible turbulence effects based on the general curvilinear coordinate systems yields the most satisfactory prediction for this complicated SDR flowfield. 36 refs.},
doi = {10.2514/3.23867},
url = {https://www.osti.gov/biblio/117649},
journal = {Journal of Propulsion and Power},
number = 3,
volume = 11,
place = {United States},
year = {Mon May 01 00:00:00 EDT 1995},
month = {Mon May 01 00:00:00 EDT 1995}
}