Internal flow simulation of enhanced performance solid rocket booster for the Space Transportation System

Ahmad, Raza; McCool, Alex

doi:10.2514/6.2001-3585

Cited by 4 publications

(4 citation statements)

References 24 publications

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“…Three turbulence models were utilized in this study and are given in Table 2. The calculated values of y + on a fine grid of size 324300 cells [8] were in the range 0.5 to 8 with some scatter due to high values of cell aspect ratios; therefore, the desired wall y + levels were not fully achieved. The size of this motor is large; consequently, axial refinements were not pursued because they were cost and time prohibitive [8].…”

Section: Turbulence Quantitiesmentioning

confidence: 99%

“…This analysis was performed to maintain a continuity with previous analyses [3][4][5][6][7][8] of this motor; serve as a non-vectored baseline for any three-dimensional vectored nozzles; provide a relatively simple application and test for various CFD solution schemes, grid sensitivity studies, and turbulence heat transfer/modeling; and calculate the nozzle convective heat transfer coefficients. The purpose of this study was to determine the convective heat transfer in the RSRM.…”

Section: Introductionmentioning

confidence: 99%

“…At this time, it is not known how convective heat transfer is affected by the trajectory and impingement of the slag particles. Details of this study are given in [8]. It involved two-phase flow where slag concentration, accretion rates, and particle trajectories were calculated.…”

Section: Introductionmentioning

confidence: 99%

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Convective Heat Transfer in the Reusable Solid Rocket Motor of the Space Transportation System

Ahmad

2005

Heat Transfer Engineering

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Section: Turbulence Quantitiesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Convective Heat Transfer in the Reusable Solid Rocket Motor of the Space Transportation System

Ahmad

2005

Heat Transfer Engineering

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“…In spite of this development, radiation is not always incorporated into the internal flow simulation in a solid rocket motor with a metallized propellant [10,11]. One reason is the dramatic CPU time increase by inclusion of the radiation, especially when an exact intensity field is intended.…”

mentioning

confidence: 95%

Radiative Heat Transfer Analysis with Molten Al2O3 Dispersion in Solid Rocket Motors

Jung

Brewster

2008

Journal of Spacecraft and Rockets

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Radiative heat transfer by alumina smoke particles (molten Al 2 O 3 ) in aluminized solid rocket motor internal flowfields has been investigated by computational simulation. The issue of how to define the alumina dispersion's radiative properties has been addressed to be compatible with existing radiative transfer equation solvers. Individual particleradiativeproperties,whicharenongrayandanisotropicinscattering,areevaluatedfromfundamentalparticle scattering theory for spheres (i.e., Mie theory) and optical constants from the literature, including temperature and spectraldependence.Anintegration procedure overwavelength hasbeenimplemented tomakeuseoftheeffective gray form of two common radiative transfer equation solvers: the finite volume method and Rosseland diffusion radiation model. The internal flowfield has beenmodeled including turbulent multiphase flow with inert radiating particles using commercial computational fluid dynamics software. The simulation has been exercised for a subscale solid rocket motor,the75-lbballistictestandevaluationsystemsmotor.Simulationresultsshowthatthebulkoftheinternalflowfield (the core flow) is very optically thick, so much so as to be amenable to Rosseland diffusion modeling. Nomenclature A= projected area a = absorption coefficient D = particle diameter, m fT = blackbody fractional function f pn = particle-scattering factor I = intensity K eI;R = Rosseland extinction coefficient k = absorption index N = particle number density n = refractive index Q a = absorption efficiency Q e = extinction efficiency Q s = scattering efficiency r = particle radius r = position vector s = direction vector s 0 = scattering direction vector T = particle temperature T e = blackbody irradiation temperature V = volume pn = particle extinction efficiency (Rosseland mean) " pn = particle emissivity = single-scattering particle polar angle pn = particle reflectivity p = particle-scattering coefficient = Stefan-Boltzmann constant (5:672 10 8 W=m 2 K 4 ) = phase function 0 = solid angle ! 0 = single-scattering albedo Subscripts a = absorption b = blackbody e = extinction I = isotropic n = particle number p = particle s = scattering = wavelength Superscripts * = nondimensional

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Numerical Analysis of Flow Inside a Solid Rocket Motor with Relation to Nozzle Inlet Ablation

Shimada

Sekiguchi²,

Sekino³

2006

36th AIAA Fluid Dynamics Conference and Exhibit

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Internal flow simulation of enhanced performance solid rocket booster for the Space Transportation System

Cited by 4 publications

References 24 publications

Convective Heat Transfer in the Reusable Solid Rocket Motor of the Space Transportation System

Convective Heat Transfer in the Reusable Solid Rocket Motor of the Space Transportation System

Radiative Heat Transfer Analysis with Molten Al2O3 Dispersion in Solid Rocket Motors

Numerical Analysis of Flow Inside a Solid Rocket Motor with Relation to Nozzle Inlet Ablation

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