Results 211 to 220 of about 13,320 (264)

Design of Rocket Engine Nozzle Using Method of Characteristics

R. S. Tarnacha
openalex   +1 more source

Perspectives of Additive Manufacturing in 5.0 Industry. [PDF]

Materials (Basel)
Sala D, Richert M.
europepmc   +1 more source

Influence of rocket design parameters on engine nozzle efficiencies [PDF]

30th Joint Propulsion Conference and Exhibit, 1994
Using a modified version of JANNAFs Two-Dimensional Kinetic Program (TDK), parametric calculations of rocket nozzles were performed. Efficiencies of energy release in rocket engines are defined. The domain of nozzle losses is classified by two-dimensionality, frictionand kinetic.
Hagemann, G., Manski, D.
openaire   +4 more sources

Some of the next articles are maybe not open access.

Related searches:

Electrification of nozzle in a liquid rocket engine

Combustion, Explosion, and Shock Waves, 1995
A method of electrical-physical diagnostics is developed and experimental studies are conducted of the process of nozzle electrification in a liquid rocket engine operating on a hydrocarbon fuel. The highest electric potential is shown to be realized at about a stoichiometric ratio of the components, i.e., when the flow velocity, temperature, and ...
A. V. Voronetskii, N. M. Pushkin, D. A. Yagodnikov   +2 more
openaire   +2 more sources

Performance prediction and optimization for liquid rocket engine nozzle [PDF]

Aerospace Science and Technology, 2007
An optimization approach, based on computational fluid dynamics methodology, is investigated for the performance prediction and optimization of liquid rocket engine nozzle. The CFD code employs implicit Lower-Upper decomposition (LU) scheme for solving the two-dimensional axisymmetric Navier–Stokes (NS) equations and species transport equations in an ...
Jie Fang, Xu Xu, Minghao Liu, Cai Guobiao   +3 more
openaire   +1 more source

Simulation of a Rocket Engine Nozzle Discharge Coefficient

Russian Aeronautics, 2018
Multiparameter studies of the discharge coefficient dependence on the nozzle geometry and the presence of a condensed phase in combustion products were performed. The simulation results obtained satisfactorily agree with the well-known generalized data.
K. S. Titov, A. I. Glazunov, A. N. Sabirzyanov, A. N. Kirillova   +3 more
openaire   +2 more sources

Numerical Analysis of Nozzle Material Thermochemical Erosion in Hybrid Rocket Engines [PDF]

Journal of Propulsion and Power, 2012
Ablative materials are commonly used to protect the nozzle metallic housing and to provide the internal contour to expand the exhaust gases in both solid and hybrid rockets. Because of interaction with hot gas, these materials are chemically eroded during rocket firing, with a resulting nominal performance reduction.
BIANCHI, DANIELE, NASUTI, Francesco
openaire   +3 more sources

Inviscid Nozzle for Aerospike Rocket Engine Application

Applied Mechanics and Materials, 2015
A computational method for the steady 2-D flow in axially symmetrical rocket nozzles with a given profile is developed, in order to determine the Maximum thrust contour of rocket engine nozzles with large expansion ratio. The optimized nozzles proved a more than 10% increase in the integral specific impulse recorded during the variable ...
Florin Radu Bacaran, Mihai Predoiu, Valentin Ionut Misirliu, Radu D. Rugescu, Alina Bogoi   +4 more
openaire   +2 more sources

Performance of the aerobell extendible nozzle rocket engine

7th Aerospace Sciences Meeting, 1969
Aerobell extendible nozzle rocket engine design and performance, cold flow and simulated hot flow test ...
R. R. Stromsta, G. A. Hosack
openaire   +2 more sources