Analysis of Convective Heat Transfer in Rocket Nozzles

Mayer, E.

doi:10.2514/8.5675

Cited by 45 publications

(13 citation statements)

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“…The three modes of heat transfer occurring between the combusion products and the nozzle wall are due to convection, radiation, and particle impingement. Con- vective heat transfer in rocket nozzles can be accurately computed using methods developed by Bartz [7,8] and Mayer [9]. The methodology to calculate the radiation of the gas-particle cloud in a solid propellant nozzle is presented in references [ 10,131.…”

Section: Methods Of Analysismentioning

confidence: 99%

Heat Transfer Studies on a Rocket Nozzle for Naval Application

Das

Moore

Boyer

1988

Naval Engineers Journal

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where he performed studies on rocket nozzles and aerodynamic heating for the Navy's missile program. Dr. Glen R. Moore received his B.S. degree in mechanical engineering from Wichita State University in I967 and his M.S. and Ph.D. degrees in mechanical engineering from Arizona State University in 1969 and 1971. Since 1971 he has been employed by the Naval Surface Weapons Center, Dahlgren, Virginia. He has been extensively involved in the analysis and testing of Navy gun and mkile system launch environments and their effects on personnel, equipment, and ships. Dr. Moore has authored numerous reports and papers on gun blast and rocket motor plume environments. He is currently a member of the JANNAF Exhaust Plume Technology Subcommittee. Dr. Charles T. Boyer received his B.S., M.S. and Ph.D. degrees from Virginia Polytechnic Institute and State University in 1969, I971 and 1984. He served as an intelligence officer and battery commander in the U.S. Army from 1971 until 1973 in Germany. Since 1974 he has worked at the Naval Surface Weapons Center, Dahlgren, Virginia. He was involved with the analysis and design of gun propelling charge assemblies and with the analysis and measurement of heat transfer from these charge assemblies to the gun bore from 1974 through 1980.Since 1980, he has analyzed and measured the heat transfer from rocket exhaust plumes to ablators used to protect ships and their equipment. He has also analyzed the in-depth heat transfer in these ablators. Currently, Dr. Boyer is the project manager for the generic booster/vertical launching system compatibility test program. He has authored numerous reports and papers on all of this work. ABSTRACTHeat transfer results are presented here for a rocket nozzle that uses aluminized solid propellant. The Solid Performance Computer Program (SPP) was employed to calculate the twodimensional, two-phase flow properties inside the nozzle. Utilizing the properties of particle phase obtained from this program, calculations were made for the heat flux due to particle impingement. Predictions are also presented for convective and radiative heat transfer along the nozzle surface. A comparison was made to assess the magnitudes of various modes of heat transfer. The methodology and results presented in this paper should provide useful data to designers of new rocket nozzles and should aid studies to improve the design of existing nozzles.

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Section: Methods Of Analysismentioning

confidence: 99%

Heat Transfer Studies on a Rocket Nozzle for Naval Application

Das

Moore

Boyer

1988

Naval Engineers Journal

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“…Por el contario, en las paredes longitudinales del ducto se tiene una condición de tipo Neumann [2], es decir, -k ∂T/∂y = 0, que emula las condiciones reales de operación dado que en motores cohetes las toberas presentan aislantes térmicos de alto desempeño para evitar pérdidas de energía [24]. Es importante mencionar que el valor de h se recupera de [25] y los demás valores de [18] para las condiciones dadas.…”

Section: B Modelo Matemáticounclassified

Modelación de la distribución térmica en una tobera convergente-divergente utilizada en sistemas aeroespaciales

Alvarez-Montoya¹,

Sierra²,

Navia³

et al. 2019

Proceedings of the 17th LACCEI International Multi-Conference for Engineering, Education, and Technology: “Industry, Innovation

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A numerical mathematical model was developed to determine the behavior of thermal distribution in a convergentdivergent nozzle used in aerospace applications. This development was carried out by using the two-dimensional heat equation for describing the phenomenon, which was resolved by means of the finite difference method. In addition, it was considered insulated and flow boundary conditions, a structured mesh with, and a nodal density of 169. The methodology was implemented in MATLAB through an algorithm which allows variations in the geometry, nodal density, and inlet conditions. This methodology was validated using computational fluid dynamics (CFD). The validation demonstrated that the proposed methodology reduces the computational cost by having an execution time 1555 times less than CFD simulation time. The relative error between the methodology and the CFD results was 2,9 %. The proposed methodology would allow the preliminary design process of this type of nozzles by analyzing thermal distribution effectively and accurately.

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“…Due to aerodynamic interactions, the perturbations grow in magnitude and reach a maximum value. When the dynamic pressure (ρ a U 2 a /2) of the air stream in air-blast atomization is large enough, the amplitude of the surface waves will grow if their wavelength (λ) exceeds a minimum value [23][24][25][26]. There exists a dominant or most unstable wave number corresponding to the maximum growth rate and when the amplitude of the disturbance reaches a critical value, the wave detaches from the sheet to form shreds or ligaments, which rapidly collapse, forming drops.…”

Section: Wave Mechanisms and Size Distributionmentioning

confidence: 99%