Abstract
The fuel of rocket engine can improve the cooling process of chamber and nozzle walls by means of Kerosene-alumina nanoliquid. In particular this investigation is devoted to explore the credible potential use of kerosene-Al2O3 nano-liquid for thrust chamber regenerative cooling in semi-cryogenic rocket engine due to its enhanced thermal properties. Mixed convection boundary layer plane Poiseuille flow in horizontal channel under the variable thermal conductivity and inclined magnetic field are taken into account. The spherical shaped Alumina (Al2O3) nano-size particles with volume fraction (0.01, 0.02, 0.03 and 0.04) are suspended in kerosene oil carrier liquid. The governing flow problem consists of nonlinear coupled differential equations is tackled by analytical technique. Influence of various evolving pertinent parameters is examined graphically. The role of physical parameters of contemporary interest like Eckert number, Grashof number, thermal radiation, heat source/sink, Nusselt number and Skin-friction are numerically investigated and presented in tabular form. Convergence of obtained series solutions has been deliberated by "h" and the square error norm 2 curves are also presented in each case. (C) 2018 Elsevier B.V. All rights reserved.