Modified Adomian decomposition mechanism for hybrid nanofluid flow through rocket engine nozzle based CoFe2O4 and Ag nanoparticles

The principal aim of the contemporary investigation is to examine the influences of a hybridized nanofluid using Cobalt ferrite and silver gold nanoparticles in a nozzle of rocket engine. Moreover, the contribution of the dissipative heat alongside the impact of thermal radiation energises the heat transport phenomenon. It has diverse industrialized implementations involving aeronautical engineering and the modeling of polymerized melts. In the context of mathematical modeling, using the correspondence alteration method (similarity transformation), the leading equations were renewed into a system of nonlinear ODEs. This issue is handled semi-analytically by utilizing the Modified Adomian Decomposition Method (MADM) in the MATLAB program to study the influence of relevant physical factors. The temperature and velocity profile graphs for important quantities are shown, as well as the logical and physical reasoning behind them. Verification is also performed to confirm the executed experiments. The results show Reynolds number clearly affects the flow speed of the nanofluid, as the speed declines immediate the side layer or the surface of the missile containing the nanofluid. A large heat flow, which upsurges the temperature and expands the boundary layer, is caused by an increment in the radiation parameter and Eckert number. The viscosity of nanoparticles increases, and the effect is more extensive if both nanoparticles volume fraction increases. The effect of cobalt ferrite nanoparticles is more noticeable than the consequence of silver nanomolecules on the relative heat capacity of the nanofluid. The surface friction of the hybridized nanofluid flow declines with the potential parameters studied. Rising the Eckert number reduces the heat transfer ranks of the nano-fuel.