Characteristic-based algorithms for flows in thermo-chemical nonequilibrium

Walters, Robert W.; Cinnella, Pasquale; Slack, David C.; Halt, David W.

doi:10.2514/6.1990-393

Cited by 28 publications

(15 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The Loci-CHEM [21][22] CFD flow solver developed by Mississippi State can compute chemically reacting mixtures of thermally perfect gases on three-dimensional, mixed element unstructured mesh. Loci-CHEM is a finite volume, Navier-Stokes flow solver with a finite rate and equilibrium chemistry.…”

Section: Comparison With Loci-chem Real Gas Solutionmentioning

confidence: 99%

Establishing Approaches to Modeling the Ares I-X and Ares I Roll Control System with Free-Stream Interaction

Pao

Deere

Abdol-Hamid

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

Approaches were established for modeling the roll control system and analyzing the jet interactions of the activated roll control system on Ares-type configurations using the USM3D Navier-Stokes solver. Components of the modeling approach for the roll control system include a choice of turbulence models, basis for computing a dynamic equivalence of the real gas rocket exhaust flow in terms of an ideal gas, and techniques to evaluate roll control system performance for wind tunnel and flight conditions. A simplified Ares I-X configuration was used during the development phase of the roll control system modeling approach. A limited set of Navier-Stokes solutions was obtained for the purposes of this investigation and highlights of the results are included in this paper. The USM3D solutions were compared to equivalent solutions at select flow conditions from a real gas NavierStokes solver (Loci-CHEM) and a structured overset grid Navier-Stokes solver (OVERFLOW). NomenclatureA e = thruster exit area, in.

show abstract

Section: Comparison With Loci-chem Real Gas Solutionmentioning

confidence: 99%

Establishing Approaches to Modeling the Ares I-X and Ares I Roll Control System with Free-Stream Interaction

Pao

Deere

Abdol-Hamid

2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

show abstract

“…GASP is capable of solving the full Reynolds-averaged Navier-Stokes (RANS) equations as well as subsets of those equations, including the thin-layer Navier-Stokes (TLNS), PNS, and Euler equations 5 . The program is a finite volume code which utilizes the upwind/relaxation algorithms.…”

Section: Computational Analysismentioning

confidence: 99%

“…Both the Euler and PNS solutions were initialized using the experimental pressure data at the entrance plane boundary. Roe's flux difference scheme was used in the crossflow plane; a minmod flux limiting scheme was used to restrict higher order terms in the crossflow plane; and an implicit LU decomposition scheme was used for time integration 5 . A tangency boundary condition was imposed on solid walls for the Euler solutions, while a no-slip boundary condition with a fixed wall temperature of 90 degrees Fahrenheit was imposed for PNS solutions.…”

Section: D Proceduresmentioning

confidence: 99%

“…Several changes were made from the 2D computational procedure to obtain the 3D solutions. These include the use of Van Leer's flux vector splitting in the crossflow plane, a Van Albeda-type smooth limiter to restrict higher order terms, and the use of an approximate factorization scheme for time integration 5 . The CFL number specified was also observed to have an effect on the solution.…”

Section: D Proceduresmentioning

confidence: 99%

“…The CFL number specified was also observed to have an effect on the solution. GASP computes local time steps at each solution plane based on the CFL number specified 5 . As the grid size increased, it was necessary to lower the CFL number to obtain a well-converged solution.…”

Section: D Proceduresmentioning

confidence: 99%

See 2 more Smart Citations

Generic hypersonic inlet module analysis

Cockrell

Lawrence

1991

9th Applied Aerodynamics Conference

View full text Add to dashboard Cite

A computational study associated with an internal inlet drag analysis was performed for a generic hypersonic inlet module. The purpose of this study was to determine the feasibility of computing the internal drag force for a generic scramjet engine module using computational methods. The computational study consisted of obtaining two-dimensional (2D) and threedimensional (3D) computational fluid dynamics (CFD) solutions using the Euler and parabolized Navier-Stokes (PNS) equations. The solution accuracy was assessed by comparisons with experimental pitot pressure data. The CFD analysis indicates that the 3D PNS solutions show the best agreement with experimental pitot pressure data. The internal inlet drag analysis consisted of obtaining drag force predictions based on experimental data and 3D CFD solutions. A comparative assessment of each of the drag prediction methods is made and the sensitivity of CFD drag values to computational procedures is documented. The analysis indicates that the CFD drag predictions are highly sensitive to the computational procedure used.

show abstract

Truly two-dimensional algorithms for radiative non-equilibrium flows

Elbert

Cinnella

Thirteenth International Conference on Numerical Methods in Fluid Dynamics

View full text Add to dashboard Cite

Characteristic-based algorithms for flows in thermo-chemical nonequilibrium

Cited by 28 publications

References 2 publications

Establishing Approaches to Modeling the Ares I-X and Ares I Roll Control System with Free-Stream Interaction

Establishing Approaches to Modeling the Ares I-X and Ares I Roll Control System with Free-Stream Interaction

Generic hypersonic inlet module analysis

Truly two-dimensional algorithms for radiative non-equilibrium flows

Contact Info

Product

Resources

About