Direct and Large Eddy Simulations of Compressible Wall Injection Flows in Laminar, Transition and Turbulent Regimes

Wasistho, B.; Haselbacher, Andreas; Najjar, Fady; Tafti, Danesh K.; Balachandar, S.; Moser, Robert D.

doi:10.2514/6.2002-4344

Cited by 8 publications

(4 citation statements)

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“…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.…”

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confidence: 99%

Compressible integral representation of rotational and axisymmetric rocket flow

Akiki

Majdalani

2016

J. Fluid Mech.

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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.

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confidence: 99%

Compressible integral representation of rotational and axisymmetric rocket flow

Akiki

Majdalani

2016

J. Fluid Mech.

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“…Rather than allow these challenges to deter their activities, one must acknowledge that the CSAR scientists have chosen the course of continual improvement in their quest for a systemic code. In the absence of suitable experimental data for validation purposes, these investigators 54 have resorted to expeditious, limiting process verifications based on the approximate solution obtained by Majdalani and Van Moorhem. 8 This solution is identical in scope to the one under scrutiny.…”

Section: -2-american Institute Of Aeronautics and Astronauticsmentioning

confidence: 99%

Some Recent Developments in Rocket Core Dynamics

Majdalani

Flandro

2003

39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit

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Here we describe some recent developments in analytical models that have been formulated in support of numerical and experimental studies of core gas dynamics appropriate of idealized rocket chambers. These analytical pursuits have invariably helped in providing additional physical insight while unraveling concrete parametric relations, explicit solutions, and group parameters of fundamental importance. In several practical applications, they have been invaluable in providing limiting process benchmarks needed to verify and, thereby, validate the reliability of numerical simulations. In many instances, they have enabled the specification of key similarity parameters that have been used to guide both experimental and numerical simulations. When equipped with perturbation tools, asymptotic methods have proven particularly useful in unveiling the essential features of acoustic instability mechanisms in rocket motors and other large combustors.

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“…Otherwise the flow remains laminar. More insights about the effect of RANS models [4], compressibility effect [6] [8] or the effect of turbulence [1] were also provided. Nevertheless, improvements concerning triggering the transition process are still to be made.…”

Section: Introductionmentioning

confidence: 99%