Numerical Study of Erosive Burning in Multidimensional Solid Propellant Modeling

Topalian, Victor; Zhang, Ju; Jackson, T. L.; Isfahani, Amir H.G.

doi:10.2514/1.b34090

Cited by 9 publications

(2 citation statements)

References 27 publications

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“…Originally, the solution is developed for a propellant burning-rate behaviour that follows Saint-Robert's power law. However, in modelling erosive burning of propellants, it is useful to explore the effects of varying the velocity profile along the injecting surface (Zhang & Jackson 2010;Topalian et al 2011). This may be accomplished by first normalizing the variables P(X), X and ζ with no pressure dependency.…”

Section: Flow Driven By Oscillatory Wall Injectionmentioning

confidence: 99%

“…Naturally, the wall shearing deformation rate becomes a parameter of interest when studying such variations along solid propellant grains (Jackson 2012). As defined by Topalian et al (2011), the wall shearing rate may be evaluated as the gradient of the streamwise velocity in the normal direction to the injecting surface, (du/dy) w . In our case, figure 14 is used to compare the shear rate along the injecting surface for uniform wall injection as well as two undulating flows corresponding to η = 5 and 10.…”

Section: Flow Driven By Oscillatory Wall Injectionmentioning

confidence: 99%

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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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Section: Flow Driven By Oscillatory Wall Injectionmentioning

confidence: 99%

Section: Flow Driven By Oscillatory Wall Injectionmentioning

confidence: 99%