Aeroacoustic Instability in Rockets

Flandro, Gary A.; Majdalani, Joseph

doi:10.2514/2.1971

Cited by 107 publications

(81 citation statements)

References 3 publications

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“…This may be owed to its association with several studies involving hydrodynamic instability [23][24][25][26][27][28], acoustic instability [29][30][31][32][33][34][35], wave propagation [36][37][38][39], particle-mean flow interactions [40], and rocket performance measurements [41][42][43]. The Taylor-Culick solution was originally verified to be an adequate representation of the expected flowfield in SRMs both numerically by Sabnis et al [44] and experimentally by Dunlap et al [45,46], thereby confirming its character in a nonreactive chamber environment.…”

Section: Doi: 102514/1j055949mentioning

confidence: 95%

Viscous Mean Flow Approximations for Porous Tubes with Radially Regressing Walls

Saad

Majdalani

2017

AIAA Journal

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The mean gaseous motion in solid rocket motors has been traditionally described using an inviscid solution in a porous tube of fixed radius and uniform wall injection. This model, usually referred to as the Taylor-Culick profile, consists of a rotational solution that captures the bulk gaseous motion in a frictionless rocket chamber. In practice, however, the port radius increases as the propellant burns, thus leading to time-dependent effects on the mean flow. This work considers the related problem in the context of viscous motion in a porous tube and allows the radius to be time dependent. By implementing a similarity transformation in space and time, the incompressible Navier-Stokes equations are first reduced to a nonlinear fourth-order ordinary differential equation with four boundary conditions. This equation is then solved both numerically and asymptotically, using the injection Reynolds number Re and the dimensionless wall regression ratio α as primary and secondary perturbation parameters. In this manner, closedform analytical solutions are obtained for both large and small Reynolds number with small-to-moderate α. The resulting approximations are then compared with the numerical solution obtained for an equivalent third-order ordinary differential equation in which both shooting and the irregular limit that affects the fourth-order formulation are circumvented. This code is found to be capable of producing the stable solutions for this problem over a wide range of Reynolds numbers and wall regression ratios.

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Section: Doi: 102514/1j055949mentioning

confidence: 95%

Viscous Mean Flow Approximations for Porous Tubes with Radially Regressing Walls

Saad

Majdalani

2017

AIAA Journal

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“…It is usually referred to as the Taylor-Culick profile and remains one of the most cited models in rocket motor analysis. For example, Chedevergne et al (2006), Abu-Irshaid et al (2007), Griffond et al (2000), Beddini (1986) and Flandro & Majdalani (2003) made extensive use of the Taylor-Culick model as a basis for their instability work.…”

Section: Relevance To Propulsion Systemsmentioning

confidence: 99%

Internal Flows Driven by Wall-Normal Injection

Majdalani¹,

Saad²

2012

Advanced Fluid Dynamics

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“…(1). By incorporating unsteady rotational terms into the standard energy equation, a higher order model of the progression of internal energy in rocket motors has been recently proposed by Flandro and Majdalani [19]. This energy assessment involves both rotational and irrotational contributions to pressure (p) and velocity (u).…”

Section: Basic Model and Solutionmentioning

confidence: 99%

“…In the past, several estimates for this function have been provided following Culick [3][4][5][6][7][8][9][10][11][12] and Flandro [13][14][15][16][17][18][19][20]22]. Using recent methodology that takes account of rotational flow elements in the combustion chamber, our aim here is to employ the higher order expressions for the velocity and pressure fields to estimate the energy normalization function.…”

Section: Introductionmentioning

confidence: 99%

“…Using recent methodology that takes account of rotational flow elements in the combustion chamber, our aim here is to employ the higher order expressions for the velocity and pressure fields to estimate the energy normalization function. The present study will hence incorporate both acoustical and vortical effects, an approach that is becoming well recognized in the propulsion community [19]. Both cylindrical (circular-port) and slab (rectangular-port) chambers will be considered and the most accurate expression for the energy normalization function will be provided for each.…”

Section: Introductionmentioning

confidence: 99%

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