Journal ArticleDOI
Rotational axisymmetric mean flow and damping of acoustic waves in asolid propellant rocket.
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In this article, the authors used the solution for potential flow subject to the boundary conditions of no flow through the head end and uniform speed normal to the burning surface, and the result for the Mach number in a cylindrical chamber isAbstract:
.!LTHOUGH for many purposes the one-dimensional apft proximation to the steady flow in a rocket chamber is adequate, there are occasions when more precise information is required. For example, analysis of the stability of pressure oscillations involves knowledge of the streamlines. It has been common practice to use the solution for potential flow subject to the boundary conditions of no flow through the head end and uniform speed normal to the burning surface. Since the Mach number generally is very small, one may assume the density to be constant; the result for the Mach number in a cylindrical chamber isread more
Citations
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Effects of vorticity on rocket combustion stability
TL;DR: In this paper, it is shown that the creation of vorticity is due primarily to the axial unsteady pressure gradient across mean flow streamlines at the surface, and that there is a transfer of energy from the pressure oscillations (acoustic field) to the rotational waves (vorticity field).
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Solid propellant chemistry, combustion, and motor interior ballistics
TL;DR: In this article, the authors present in-depth coverage on a wide range of topics including advanced materials and non-traditional formulations; the chemical aspects of organic and inorganic components in relation to decomposition mechanisms, kinetics, combustion and modelling; safety issues, hazards and explosive characteristics; and experimental and computational interior ballistics research, including chemical information and the physics of the complex flow field.
Book
Fundamentals of Hybrid Rocket Combustion and Propulsion
TL;DR: In this paper, a review of Solid-Fuel Regression Rate Behavior in Classical And Non-Classical Hybrid Rocket Motors is presented. But the review is limited to the following:
Journal ArticleDOI
Vortex-Shedding Phenomena in Solid Rocket Motors
TL;DR: In this article, the meanings of various Strouhal number definitions are discussed and the basic mechanisms for sound production in ducts or chambers are then discussed through simple tools, such as the linear hydrodynamic stability analysis, Flandro's method and the acoustic balance technique, which provide good insights into the physics of the phenomenon.
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Internal flow field studies in a simulated cylindrical port rocket chamber
TL;DR: In this article, the mean and fluctuating speed and turbulent shear stresses were measured in the principle coordinate directions using three-element hot-wire anemometers, showing that noticeable velocity fluctuations in the head end region generally decrease in intensity, relative to centerline speed, over the first five port diameters.
References
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Journal ArticleDOI
Test time in low pressure shock tubes
TL;DR: In this paper, the reduction of test time in low pressure shock tubes, due to a laminar wall boundary layer, has been analytically investigated, and it was found that β is considerably larger than the estimates made by Roshko and Hooker except for very strong shocks.
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Shock Tube Test Time Limitation Due to Turbulent-Wall Boundary Layer
TL;DR: In this article, the authors investigated the test time limitation due to the premature arrival of the contact surface of the boundary layer and compared the results with those for wholly laminar-wall boundary layers, and found that, for a given shock Mach number, the maximum possible test time (in a long shock tube) varies as d 6/4p co1/4 and d2p CD for both air and argon.
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The Tailored-Interface Hypersonic Shock Tunnel
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Effect of boundary-layer growth in a shock tube on shock reflection from a closed end
TL;DR: In this paper, the theory of the flow field behind the incident shock is modified to allow for effects in addition to boundary layer growth which cause deviations from an ideal shock tube flow.