In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region ( including stagnation line and sonic line).

Before this only the firstorder scheme and loosely coupledmethod was successfully used in this research field. The gais model for chemically relaxingair consists of seven species(O,O_2,NO,N,NO￣(+),N_2,e￣(-))and seven substantial reactionsare considered. The calculated results are compared with existing numerical solutions solvedby first-order scheme in the literature along the stagnation line of the hemisphere,improvedresuIts are obatined.

The steady state simulations were performed on a one meter nose radius sphere at an altitude of 65 km and at free stream velocity of 8km/s , and the distribution of the temperature and mass fraction of species along the stagnation line , the wall temperature and heat transfer rate were obtained at two attack angles of flight ( α =0° and α =5°),and the data at an attack angle of zero were compared well with references.

Numerical solutions of flow and heat transfer process on the unsteady flow of a compressible viscous fluid with variable gas properties in the vicinity of the stagnation line of an infinite swept cylinder are presented.

Unsteady compressible boundary layer flow on the stagnation line of an infinite swept cylinder

Investigation of swirling flow of a viscous gas near the stagnation line of a blunt body

Profiles of the rotational temperature along the stagnation line in the case of transverse flow over a cylinder are obtained.

Investigation of the system of equations for a compressible laminar boundary layer in the neighborhood of a stagnation line

In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region ( including stagnation line and sonic line). Seven species (N2, O2, N, O, NO, NO + , e-) as well as seven chemical reaction equations of ionized air are considered. It is assumed that the chemical reactions proceed at finite rate, a binary diffusion model is used for nonequilibrium diffusion. Different boundary conditions are computed, including...

In this paper, the nonequilibrium viscous shock layer equations have been used to calculate the hypersonic flows over blunt bodies in the fore-body region ( including stagnation line and sonic line). Seven species (N2, O2, N, O, NO, NO + , e-) as well as seven chemical reaction equations of ionized air are considered. It is assumed that the chemical reactions proceed at finite rate, a binary diffusion model is used for nonequilibrium diffusion. Different boundary conditions are computed, including shock slip, wall slip, fully catalytic and noncatalytic wall conditions. The parameters of flowfield and electron density distributions are obtained and compared with relevant references.

The chemical equilibrium viscous shock-layer equations at stagnation line are solved numerically in this paper. The effects of radiation and mass injection are considered. The detailed line and continuum radiation models are included. The flowfield is devided into two zone as the surface mass injected, one is from the surface to v= 0 in which contains the injected species, and the other is from v= 0 to the shock in which there are no injected species.The minimum free energy method is used in determining...

The chemical equilibrium viscous shock-layer equations at stagnation line are solved numerically in this paper. The effects of radiation and mass injection are considered. The detailed line and continuum radiation models are included. The flowfield is devided into two zone as the surface mass injected, one is from the surface to v= 0 in which contains the injected species, and the other is from v= 0 to the shock in which there are no injected species.The minimum free energy method is used in determining the species concentrations. The effects of different injection rates, nose radius and free stream velocities on the convective and radiative heat transfer are discussed. The results are compared with those from references and they agree quite well with each other.

An explicit second-order upwind TVD scheme by H.C.Yee is first suc-cessfully extended to solve the viscous,diffussive,nonequilibrium,ionizing,hypersonic flowfields over a hemi-sphere.The governing gas-dynamic and species-continuity equations forlaminar flow are presented.The gas-dynamics/species continuity equations fully couplingprocedure is described in detail.Before this only the firstorder scheme and loosely coupledmethod was successfully used in this research field.The gais model for chemically relaxingair...

An explicit second-order upwind TVD scheme by H.C.Yee is first suc-cessfully extended to solve the viscous,diffussive,nonequilibrium,ionizing,hypersonic flowfields over a hemi-sphere.The governing gas-dynamic and species-continuity equations forlaminar flow are presented.The gas-dynamics/species continuity equations fully couplingprocedure is described in detail.Before this only the firstorder scheme and loosely coupledmethod was successfully used in this research field.The gais model for chemically relaxingair consists of seven species(O,O_2,NO,N,NO￣(+),N_2,e￣(-))and seven substantial reactionsare considered.The calculated results are compared with existing numerical solutions solvedby first-order scheme in the literature along the stagnation line of the hemisphere,improvedresuIts are obatined.