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Rocket engine nozzle

About: Rocket engine nozzle is a research topic. Over the lifetime, 2282 publications have been published within this topic receiving 21444 citations. The topic is also known as: rocket nozzle.


Papers
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Book
01 Jan 1963
TL;DR: In this paper, the authors defined and defined the fundamentals of solid propellant rocket propulsion systems, including propulsion system design, propulsion system parameters, and propulsion system performance analysis, as well as propulsion system testing.
Abstract: Classification definitions and fundamentals nozzle theory and thermodynamic relations flight performance chemical rocket propellant performance analysis liquid propellant rocket engine fundamentals liquid propellants thrust chambers combustion of liquid propellants turbopumps, engine design, engine controls, calibration, integration and optimization solid propellant rocket fundamentals solid propellants combustion of solid propellants solid rocket components and motor design hybrid propellant rockets thrust vector control selection of rocket propulsion systems rocket exhaust plumes electric propulsion rocket testing.

2,366 citations

D. T. Harrje1
01 Jan 1972
TL;DR: In this paper, the extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed, both theoretical and experimental, with emphasis on fundamental principles and relationships between alternative approaches.
Abstract: The solution of problems of combustion instability for more effective communication between the various workers in this field is considered. The extent of combustion instability problems in liquid propellant rocket engines and recommendations for their solution are discussed. The most significant developments, both theoretical and experimental, are presented, with emphasis on fundamental principles and relationships between alternative approaches.

418 citations

Book
01 Jan 1956
TL;DR: In this paper, a theoretical analysis of combustion instability in liquid rocket motors is presented, where the authors present a theoretical model of the combustion instability of a single-stage liquid rocket.
Abstract: : The report presents a theoretical analysis of combustion instability in liquid rocket motors.

388 citations

Book
01 Jan 1963
TL;DR: In this paper, the authors defined and defined nozzle theory and Thermodynamic Relations Heat Transfer Flight Performance Thermo-Chemical Rocket Propellant Performance Analysis Liquid Propellants Rocket Engine Engine Fundamentals Liquid Proppellants Combustion of Liquid Propulsion Systems Rocket Exhaust Plumes Rocket Testing.
Abstract: Classification Definitions and Fundamentals Nozzle Theory and Thermodynamic Relations Heat Transfer Flight Performance Thermo-Chemical Rocket Propellant Performance Analysis Liquid Propellant Rocket Engine Fundamentals Liquid Propellants Combustion of Liquid Propellants Liquid Propellant Rocket Engine Systems and Components Solid Propellant Rocket Fundamentals Solid Propellants Combustion of Solid Propellants Solid Propellant Components and Motor Design Hybrid Propellant Rockets Thrust Vector Control Selection of Rocket Propulsion Systems Rocket Exhaust Plumes Rocket Testing.

288 citations

Journal ArticleDOI
TL;DR: In this article, an empirical expression for the drag coefficient of a spherical particle in flow regimes such as occur in solid propellant rocket exhausts is presented, and the effects of these relationships on computed particle velocities and temperatures are shown.
Abstract: An empirical expression for the drag coefficient of a spherical particle in flow regimes such as occur in solid propellant rocket exhausts is presented. In these flows, typical particle Mach numbers will be below 2, and particle Reynolds numbers will range from less than 10 to greater than 100. Also, available heat-transfer relationships are applied to the gasparticle nozzle flow case. The effects of these relationships on computed particle velocities and temperatures are shown. In the cases considered, inertial and compressibility effects dominate for large particles and high chamber pressures, causing the thermal and velocity lags to be less than those predicted under a Stokes flow assumption. However, for small particles and low chamber pressures, rarefaction effects dominate, and the Stokes flow assumption leads to low estimates of particle lag.

259 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202321
202236
202124
202032
201935
201827