Full-Physics Large-Scale Multiphase Large Eddy Simulations of Flow Inside Solid Rocket Motors

Najjar, Fady; Ferry, Jim; Wasistho, B.; Balachandar, S.

doi:10.2514/6.2002-4343

Cited by 20 publications

(6 citation statements)

References 0 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…8,9 It is used in compressible flow simulations of the internal flowfield in solid rocket motors by Cheng, Liu and Sirignano, 10 Jackson, Najjar and Buckmaster, 11 and Stewart et al 12 It appears in one segment of Rocflu, a compressible Navier-Stokes solver intended for simulating rocket internal ballistics. [11][12][13][14] It is also used in characterizing turbomachinery, [15][16][17] scarfed and contoured-plug nozzles, 18,19 pulse detonation engines, 20,21 and magnetohydrodynamic systems. 22 More recently, it has been employed in applications of constructal theory by Bejan, 23 and in modeling micro-thrusters and micro-combustors by Leach 24 and Tosin et al 25 Its popularity as a simple design tool lies in its ability to predict the area ratio needed to produce a desired exit flow Mach number.…”

Section: Introductionmentioning

confidence: 99%

Modeling Mach Number and Temperature Distributions in Supersonic Nozzle Flow

Majdalani¹,

Maicke²

2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

Section: Introductionmentioning

confidence: 99%

Modeling Mach Number and Temperature Distributions in Supersonic Nozzle Flow

Majdalani¹,

Maicke²

2010

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

“…Given the relevance of an accurate mean-flow description to the study of hydrodynamic instability in simulated rocket motors, the problem was revisited by Venugopal, Najjar & Moser (2001) and, in complementary work, by Wasistho, Balachandar & Moser (2004). As a windfall, the compressible solutions engendered in these studies became valuable resources in the limiting process verification of Navier-Stokes solvers (Wasistho et al 2002;Najjar et al 2003). This was partly caused by the obstacles placed against the acquisition of rocket-related experimental data and, partly, because of the harsh, intrusion-resistant medium arising in highly pressurized and reactive chambers.…”

mentioning

confidence: 99%

Compressible integral representation of rotational and axisymmetric rocket flow

Akiki

Majdalani

2016

J. Fluid Mech.

View full text Add to dashboard Cite

This work focuses on the development of a semi-analytical model that is appropriate for the rotational, steady, inviscid, and compressible motion of an ideal gas, which is accelerated uniformly along the length of a right-cylindrical rocket chamber. By overcoming some of the difficulties encountered in previous work on the subject, the present analysis leads to an improved mathematical formulation, which enables us to retrieve an exact solution for the pressure field. Considering a slender porous chamber of circular cross-section, the method that we follow reduces the problem's mass, momentum, energy, ideal gas, and isentropic relations to a single integral equation that is amenable to a direct numerical evaluation. Then, using an Abel transformation, exact closed-form representations of the pressure distribution are obtained for particular values of the specific heat ratio. Throughout this effort, Saint-Robert's power law is used to link the pressure to the mass injection rate at the wall. This allows us to compare the results associated with the axisymmetric chamber configuration to two closed-form analytical solutions developed under either one-or two-dimensional, isentropic flow conditions. The comparison is carried out assuming, first, a uniformly distributed mass flux and, second, a constant radial injection speed along the simulated propellant grain. Our amended formulation is consequently shown to agree with a one-dimensional solution obtained for the case of uniform wall mass flux, as well as numerical simulations and asymptotic approximations for a constant wall injection speed. The numerical simulations include three particular models: a strictly inviscid solver, which closely agrees with the present formulation, and both k-ω and Spalart-Allmaras computations.

show abstract

“…6,7 In large-scale numerical simulations that involve particle burning and agglomeration, average speeds and accelerations within the chamber have routinely been estimated directly from the Taylor-Culick solution. One may refer in this regard to the work of Najjar et al, 8,9 Balachandar, Buckmaster and Short, 10 as well as others. In reactive flow simulations, the Taylor-Culick solution is so valuable in estimating the bulk gas motion that it has been either built into the codes or used as a benchmark to verify computations.…”

Section: Introductionmentioning

confidence: 98%