Coupled heat transfer between a viscous shock gasdynamic layer and a transversely streamlined anisotropic half-space

The purpose of the article is to analytically solve the conjugate problem of heat transfer in a viscous shock layer on a blunt object and thermal conductivity in an anisotropic half-space. A feature of the flow around such bodies near the critical point is that in this case, the boundary layer equations are not satisfied and it is necessary to solve the Navier-Stokes equations together with the equations of continuity, state, and energy, however, in a stationary formulation of an incompressible flow. The problem of coupled heat transfer between a viscous shock gasdynamic layer and anisotropic half-space with the assumption of incompressibility of the gasdynamic flow behind the normal part of the shock wave is posed. An analytical solution to this problem is obtained with a boundary condition at the gas-solid object interface in the form of a parameter – temperature, as well as an analytical solution to the thermal conductivity problem in an anisotropic half-space with the same boundary condition.

Aero-heating modelling on the ablative noses during flight trajectory

Purpose The purpose of this paper is to present the more accurate estimation of aero-heating for the ablative 3-D noses by using the viscous shock layers and similarity of viscous boundary layer methods. Design/methodology/approach The combination of viscous shock layer, similarity of viscous boundary layer (SVBL) methods, Park ablation and Baldwin–Lomax turbulent models is presented in this paper. The proposed method reduces computational memory and run time as compared to the time marching algorithms during flight trajectory. Therefore, the space marching algorithm and finite difference method is used, and the governing equations are transferred into curvature coordinate by using the mapping terms. Findings The solving for an ogive nose during flight trajectory shows that the convergence of this technique is fast as compared to the user defined function based on the fluent solvers, program to axisymmetric regular geometry code and other research. The results of this research are validated by the mentioned research studies. The relative error for the aero-heating, species concentration of the shock layer gas mixture because of dissociation/ionization of air and surface ablation results is less than 6, 5 and 11 per cent, respectively. Research limitations/implications The required time for an aerodynamic design of hypersonic noses reduces as the induced aero-heating is one of the principal design parameters in standpoint aerodynamic, structural and other terms. The magnitude of this parameter, surface temperature and surface recess because of ablation should be corrected during flight trajectory. Social implications The results of this research are applicable for aerospace industries. Originality/value The originality of this paper is 90 per cent.

Numerical Investigation Of The Evolution Of Disturbances On A Flat Plate In A Hypersonic Flow Of A Mixture Of Vibrationally Excited Gases

The problem of the evolution of disturbances in a hypersonic viscous shock layer on a plate in the flow of a mixture of vibrationally excited carbon dioxide and nitrogen is considered by solving of the Navier – Stokes equations. Two channels of vibrational relaxation of CO2 molecules in collisions with CO2 and in collisions with N2 were taken into account by using a two-temperature model of relaxation flows in modeling the thermal nonequilibrium. The data on the dynamics of the evolution of disturbances on f flat plate in a wide range of determining parameters (attack angle α = 5÷20°, concentration of CO2 in mixture, braking temperature T0 = 2000÷4000 K) are presented in this paper.