An investigation was performed to determine the pressure transient levels and time required to reach pressure equilibrium in a regulated liquid propulsion system due to the priming of a propellant tank during system initiation. An experimental fluid flow test setup was designed and fabricated using a pressure vessel to house distilled water as a propellant simulant for liquid hydrazine and high-pressure

Combustion process inside kerosene-GOx rocket combustor with kerosene film cooling is studied, and a modeling approach is proposed. The paper suggests to use the Lagrangian particle tracking technique to model fuel film behavior while the continuous fluid is simulated via the Navier-Stokes system of Favre-averaged equations. The approach is validated over the 12 experimental regimes by the criterions

Present article aims to discuss the characteristics of Casson type nanofluid maintained to flow through porous medium over non-linear stretching surface in the perspective of heat and mass transfer developments. A Casson type incompressible viscous nanofluid passes through the given porous medium via Darcy-Forchheimer relation. Slip boundary conditions are used for velocity, temperature and concentration

The present study introduces an innovative aerodynamic redesign of an axial flow fan based on constant diffusion factor and radial equilibrium. All input design parameters such as mass flow rate, hub to tip ratio, aspect ratio, tip diameter and angular velocity are taken from NASA Rotor 67 as a conventional axial flow fan. A computer program is developed to extract the three-dimensional geometry of

The objective of the present work is to analyze the flow, heat and mass transfer characteristics in a thin nanofluid film over a heated stretched sheet in the presence of a non-uniform heat source/sink and thermal radiation. Similarity variables are used to transform the partial differential equations into a system of ordinary differential equations. The resulting system of nonlinear ordinary differential

This study investigates the steady stagnation point flow and heat transfer passes a horizontal shrinking permeable cylinder. The free stream velocity and the prescribed surface heat flux are assumed to vary linearly with the distance from a fixed point on the cylinder. The partial differential equations governing the flow and heat transfer are transformed into a system of ordinary differential equations

In this article, the variation of temperature distribution and fin efficiency in a porous moving fin of rectangular profile is studied. This study is performed using Darcy's model to formulate the governing heat transfer differential equation. The approximate analytical solution is generated using the variational iteration method (VIM). The power series solution is validated by benchmarking it against

During the last years, several thrust control systems of aerospace rocket engines have been developed. The fluidic thrust vectoring is one of them; it is simple in design and offers a substantial gain in weight and in performance. Numbers of studies that deal with this subject are conducted on cold gas flow model. It can be expected that the thermophysical properties of the gases may affect considerably

This study analyzes the second law of thermodynamic for entropy generation in an irreversible hydromagneto-micropolar flow system with non-homogenous heat generation. The non-symmetric microstructure fluid flow past a stretching sheet with saturated porous non-linear media under magnetic field influence. Ignoring the fluid particle deformation, the microstructure is assumed rigid with the viscous suspended

Transmission error (TE) in geared rotors is a predominant source of inherent excitation at the pitch point of the gear meshing. In this paper, a transverse vibration analysis is presented to study the effect of TE on geared rotors. Due to asymmetry in the TE, it is expected to have both forward and backward whirls excited during rotor whirling, which could be used for its detection. This aspect has

A numerical simulation of a single cylinder research diesel engine fuelled by natural gas and diesel oil in dual fuel mode was conducted to test the reaction mechanism presented by Li and Williams in Ref. [1] for methane ignition. The mechanism made of only 9 reactions can represent a good compromise between reduction of computational time and accuracy of results. Simulations reproduce test cases previously

The linear model of the aero gas turbine is effective in a small application range. According to this problem, the identification method for parameter uncertain linear model of aero gas turbine proposed. The identification problem is solved by calculating nonlinear programming. Considering the parameter uncertainty of the model is the critical point of this research during the optimization process